
[Federal Register Volume 82, Number 103 (Wednesday, May 31, 2017)]
[Proposed Rules]
[Pages 24903-24906]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10979]



[[Page 24903]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0520; Directorate Identifier 2016-NM-143-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 series airplanes; and 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). This 
proposed AD was prompted by reports of cracks initiating at the upper 
radius of frame (FR) 47 and a determination that the current inspection 
procedure is not reliable in detecting certain cracking of the forward 
fitting of FR 47. This proposed AD would require repetitive inspections 
to detect cracking of the upper radius of the forward fitting of FR 47, 
and related investigative actions 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 17, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
44 51; email: 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-
0520; 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-2017-0520; 
Directorate Identifier 2016-NM-143-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 AD 
2016-0150, dated July 25, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition on all. The MCAI states:

    During scheduled maintenance inspections on the fuselage, cracks 
initiating at the upper radius of frame (FR) 47 have been reported 
on several aeroplanes. Similar damage was also discovered on the 
A300 fatigue test fuselage.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the fuselage.
    Prompted by these findings, Airbus issued Service Bulletin (SB) 
A300-53-0246, SB A300-53-6029 and SB A300-53-9014 to provide 
inspection instructions and, consequently, DGAC France issued AD F-
2006-016 to require repetitive inspections and corrective action.
    Since that [French] AD was issued, further investigation led to 
the conclusion that the current ultrasonic inspection performed in 
accordance with Airbus SB A300-53-0246 Revision 06, or SB A300-53-
6029 Revision 08, or SB A300-53-9014 Revision 01, as applicable, was 
not reliable to detect deep crack going downward.
    Consequently, to ensure the crack depth is correctly measured 
whatever the crack direction, Airbus developed a new nondestructive 
testing method [eddy current] for this special detailed inspection 
(SDI) and revised the affected SBs accordingly.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD F-2006-016, which is superseded, but 
requires the accomplishment of repetitive SDI to replace the 
previously required ultrasonic inspections [and related 
investigative actions and corrective actions if necessary].

    Related investigative actions include an ultrasonic inspection for 
cracking on the forward face of forward fitting and a detailed 
inspection for cracking of the aft fitting around the fasteners. 
Corrective actions include crack repairs, modification of the sealing 
fittings and sealing shims. This proposed AD requires reporting of the 
inspection results to Airbus. 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-2017-0520.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A300-53-0246, Revision 
08, including Appendix 1, dated April 13, 2016 (for Model A300 series 
airplanes); and Airbus Service Bulletin A300-53-6029, Revision 12, 
including Appendix 1, dated April 13, 2016 (for Model A300-600 series 
airplanes). The service information describes procedures for doing an 
SDI for cracking of the FR 47 forward fitting upper radius on the left-
hand and right-hand sides of the fuselage, and related investigative 
actions and corrective actions. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section.

[[Page 24904]]

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type designs.
    This NPRM would not supersede AD 2007-26-14, Amendment 39-15316 (73 
FR 2803, January 16, 2008). Rather, we have determined that a stand-
alone AD would be more appropriate to address the changes in the MCAI. 
This NPRM would require repetitive inspections to detect cracking of 
the upper radius of the forward fitting of FR 47, and related 
investigative actions and corrective actions if necessary. 
Accomplishment of the proposed actions would then terminate all 
requirements of AD 2007-26-14 for the inspected airplane.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Although the MCAI and service information allow further flight if 
cracks are found during accomplishment of the required action, this 
proposed AD requires that any cracking be repaired before further 
flight.

Costs of Compliance

    We estimate that this proposed AD affects 132 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                                Cost on U.S.
              Action                     Labor cost       Parts cost    Cost per product          operators
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Inspection........................  19 work-hours x $85           $0  $1,615 per            $213,180 per
                                     per hour = $1,615.                inspection cycle.     inspection cycle.
Reporting.........................  1 work-hour x $85              0  $85 per inspection    $11,220 per
                                     per hour = $85.                   cycle.                inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary related 
investigative and corrective actions that would be required based on 
the results of the proposed inspection. We have no way of determining 
the number of airplanes that might need these repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Related investigative and Corrective actions..  21 work-hours x $85 per hour =            $1,835          $3,620
                                                 $1,785.
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Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is mandatory. Comments concerning the 
accuracy of this burden and suggestions for reducing the burden should 
be directed to the FAA at 800 Independence Ave. SW., Washington, DC 
20591, ATTN: Information Collection Clearance Officer, AES-200.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

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.

[[Page 24905]]

Sec.  39.13   [Amended]

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

Airbus: Docket No. FAA-2017-0520; Directorate Identifier 2016-NM-
143-AD.

(a) Comments Due Date

    We must receive comments by July 17, 2017.

(b) Affected ADs

    This AD affects AD 2007-26-14, Amendment 39-15316 (73 FR 2803, 
January 16, 2008) (``AD 2007-26-14'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, 
except airplanes that have been repaired as specified in Airbus 
Service Bulletin A300-53-0370 or Airbus Service Bulletin A300-53-
6144, as applicable.
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R and F4-622R airplanes.
    (5) Model A300 C4-605R Variant F airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracks initiating at the 
upper radius of frame (FR) 47 and a determination that the current 
inspection procedure is not reliable in detecting certain cracking 
of the forward fitting of FR 47. We are issuing this AD to detect 
and correct fatigue cracking of the FR 47 forward fitting upper 
radius on the left-hand and right-hand sides of the fuselage, which 
could propagate and result in reduced structural integrity of the 
airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Except as required by paragraph (h) of this AD: Before exceeding 
10,000 flight cycles since first flight of the airplane or within 30 
days after the effective date of this AD, whichever is later, do a 
special detailed inspection (SDI) for cracking of the FR 47 forward 
fitting upper radius on the left-hand and right-hand sides of the 
fuselage, in accordance with the Accomplishment Instructions of the 
applicable Airbus service information specified in paragraphs (g)(1) 
and (g)(2) of this AD. Repeat the inspection thereafter at intervals 
not to exceed 4,150 flight cycles, except as required by paragraph 
(j) of this AD.
    (1) Airbus Service Bulletin A300-53-0246, Revision 08, including 
Appendix 1, dated April 13, 2016.
    (2) Airbus Service Bulletin A300-53-6029, Revision 12, including 
Appendix 1, dated April 13, 2016.

(h) Initial Inspection for Airplanes Previously Inspected

    For airplanes previously inspected as specified in the 
applicable Airbus service information specified in paragraphs (h)(1) 
through (h)(6) of this AD and on which no cracking was found: Within 
4,150 flight cycles after the most recent inspection, do the 
inspection for cracking of the FR 47 forward fitting upper radius 
required by paragraph (g) of this AD.
    (1) Airbus Service Bulletin A300-53-0246, Revision 06, dated 
October 19, 2005.
    (2) Airbus Service Bulletin A300-53-0246, Revision 07, dated 
September 9, 2008.
    (3) Airbus Service Bulletin A300-53-6029, Revision 08, dated 
October 19, 2005.
    (4) Airbus Service Bulletin A300-53-6029, Revision 09, dated 
September 9, 2008.
    (5) Airbus Service Bulletin A300-53-6029, Revision 10, dated 
July 9, 2009.
    (6) Airbus Service Bulletin A300-53-6029, Revision 11, dated 
September 28, 2009.

(i) Inspections for Airplanes With Abnormal Load Events

    For airplanes on which any crack was found during any inspection 
done as specified in Airbus Service Bulletin A300-53-0246 or Airbus 
Service Bulletin A300-53-6029, as applicable, and on which any 
abnormal load event, such as hard landing or flight in excessive 
turbulence, occurred within 3 months before the effective date of 
this AD or occurs on or after the effective date of this AD: Within 
3 months after each event, accomplish an SDI for cracking of the FR 
47 forward fitting upper radius, left-hand and right-hand sides of 
the fuselage, in accordance with the applicable Accomplishment 
Instructions of the Airbus service information specified in 
paragraphs (g)(1) or (g)(2) of this AD. If, during this 3-month 
period, another abnormal load event occurs, and if no SDI has yet 
been accomplished, before further flight after the second event, 
obtain corrective action instructions from 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), and accomplish those 
instructions accordingly.

(j) Corrective Actions for Airplanes With Cracks

    If, during any SDI as required by paragraph (g), (h), or (i) of 
this AD, any crack is found: Before further flight, do the 
applicable related investigative actions and corrective actions, in 
accordance with the Accomplishment Instructions of the applicable 
Airbus service information specified in paragraphs (g)(1) or (g)(2) 
of this AD, and obtain additional corrective action instructions 
from the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA, and accomplish 
those instructions accordingly before further flight.

(k) Reporting

    Submit a report of the findings (both positive and negative) of 
each SDI inspection required by paragraphs (g), (h), and (i) of this 
AD to Airbus Service Bulletin Reporting Online Application on Airbus 
World (https://w3.airbus.com/), at the applicable time specified in 
paragraph (k)(1) or (k)(2) of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(l) Terminating Action for AD 2007-26-14

    Accomplishing any inspection required by paragraph (g) or (h) of 
this AD terminates all requirements of AD 2007-26-14 for the 
inspected airplane.

(m) 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 International Branch, send it to the attention of 
the person identified in paragraph (n)(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 EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn:

[[Page 24906]]

Information Collection Clearance Officer, AES-200.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0150, dated July 25, 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-2017-0520.
    (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 19, 2017.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10979 Filed 5-30-17; 8:45 am]
 BILLING CODE 4910-13-P


