
[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)]
[Rules and Regulations]
[Pages 39520-39523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17203]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0520; Product Identifier 2016-NM-143-AD; Amendment 
39-18995; AD 2017-17-05]
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 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 AD was 
prompted by reports of cracks initiating at the upper radius of a 
certain frame and a determination that the current inspection procedure 
is not reliable in detecting certain cracking of the forward fitting of 
the frame. This AD requires repetitive inspections to detect cracking 
of the upper radius of the forward fitting of a certain frame, and 
related investigative actions and corrective actions if necessary. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective September 25, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 25, 
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: account.airworth-eas@airbus.com; 
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-2017-0520.

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 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 
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). The NPRM published in the 
Federal Register on May 31, 2017 (82 FR 24903) (``the NPRM''). The NPRM 
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. The NPRM proposed to 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 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.
    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]

[[Page 39521]]

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 and corrective actions if necessary].

Related investigative actions include an ultrasonic inspection for 
cracking on the forward face of the forward fitting and a detailed 
inspection for cracking of the aft fitting around the fasteners. 
Corrective actions include crack repairs, and modification of the 
sealing fittings and sealing shims. This 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD 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 correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

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 
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.

Costs of Compliance

    We estimate that this AD will affect 132 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...................  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 per              $0  $85 per inspection    $11,220 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 inspection. We have no way of determining the number 
of aircraft that might need these repairs:

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

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 AD is 2120-
0056. The paperwork cost associated with this 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 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.
    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.

[[Page 39522]]

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):

2017-17-05 Airbus: Amendment 39-18995; Docket No. FAA-2017-0520; 
Product Identifier 2016-NM-143-AD.

(a) Effective Date

    This AD is effective September 25, 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 occurs 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 Section, Transport Standards Branch, 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 and corrective actions, in 
accordance with the Accomplishment Instructions of the applicable 
Airbus service information specified in paragraph (g)(1) or (g)(2) 
of this AD, and obtain additional corrective action instructions 
from the Manager, International Section, Transport Standards Branch, 
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 Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this

[[Page 39523]]

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 (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 
Section, Transport Standards Branch, 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: 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 Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 
425-227-2125; fax: 425-227-1149.

(o) 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 A300-53-0246, Revision 08, including 
Appendix 1, dated April 13, 2016.
    (ii) Airbus Service Bulletin A300-53-6029, Revision 12, 
including Appendix 1, dated April 13, 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: account.airworth-eas@airbus.com; 
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 August 8, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-17203 Filed 8-18-17; 8:45 am]
 BILLING CODE 4910-13-P


