Airworthiness Directives; Airbus Airplanes

[Federal Register Volume 82, Number 75 (Thursday, April 20, 2017)]
[Rules and Regulations]
[Pages 18547-18550]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06712]



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Rules and Regulations
                                                Federal Register
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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. 

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Federal Register / Vol. 82, No. 75 / Thursday, April 20, 2017 / Rules 
and Regulations

[[Page 18547]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9192; Directorate Identifier 2016-NM-038-AD; 
Amendment 39-18845; AD 2017-07-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-200, A330-300, A340-200, and A340-300 series 
airplanes. This AD was prompted by a report of cracking at fastener 
holes located at a certain frame on the lower shell panel junction. 
This AD requires repetitive inspections of certain fastener holes, and 
related investigative and corrective actions if necessary. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective May 25, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 25, 2017.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email [email protected]; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9192.

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-2016-
9192; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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 A330-
200, A330-300, A340-200, and A340-300 series airplanes. The NPRM 
published in the Federal Register on October 25, 2016 (81 FR 73357) 
(``the NPRM''). The NPRM was prompted by a report of cracking at 
fastener holes located at a certain frame on the lower shell panel 
junction. The NPRM proposed to require repetitive inspections of 
certain fastener holes, and related investigative and corrective 
actions if necessary. We are issuing this AD to detect and correct 
cracking at frame 40 on the lower shell panel junction; such cracking 
could lead to reduced structural integrity of the fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0136, dated June 13, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330, A340-200, and A340-300 series airplanes. The MCAI states:

    During A330/A340 aeroplanes full scale fatigue test specimen in 
the FR40-to-fuselage skin panel junction, fatigue damage has been 
found. Corrective actions consisted of the following actions:

--In-service installation of an internal reinforcing strap on 
related junction required by DGAC [Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC)] France AD 1999-448-126(B) and [DGAC 
France] AD 2001-070(B),
--retrofit improvement of internal reinforcing strap fatigue life 
through recommended Airbus Service Bulletin (SB) A330-53-3145, and
--new design in production through Airbus modification 44360.

    The aeroplanes listed in the Applicability section of this 
[EASA] AD are all aeroplanes post-mod 44360 and pre-mod 55792 
(fuselage reinforcement at FR40 in production).
    Recently, during embodiment of a FR40 web repair on an A330 
aeroplane and during FR40 keel beam fitting replacement on an A340 
aeroplane, the internal strap was removed and rototest inspection 
was performed on several holes.
    Cracks were found on both left-hand (LH) and right-hand (RH) 
sides on internal strap, or butt strap, or keel beam fitting, or 
forward fitting FR40 flange.
    This condition, if not detected and corrected, could lead to 
crack propagation, possibly resulting in reduced structural 
integrity of the fuselage.
    For the reasons described above, this [EASA] AD requires 
repetitive rototest inspections of 10 fastener holes located at FR40 
lower shell panel junction on both LH and RH sides, and, depending 
on findings, accomplishment of the applicable corrective actions 
[which include oversizing, installing fasteners and repair; and 
accomplishment of applicable related investigative actions, which 
include a rototest inspection for cracking after oversizing].

    The compliance time ranges between 20,000 flight cycles or 65,400 
flight hours and 20,800 flight cycles or 68,300 flight hours, depending 
on airplane utilization and configuration. The repetitive inspection 
interval ranges between 14,000 flight cycles or 95,200 flight hours and 
24,600 flight cycles or 98,700 flight hours, depending on airplane 
configuration. 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-2016-9192.

[[Page 18548]]

Comments

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

Request To Refer to Revised Service Information

    Delta Airlines (DAL) requested that we revise paragraphs (g), 
(g)(1), and (g)(2) of the proposed AD to refer to Airbus Service 
Bulletin A330-53-3215, Revision 02, dated November 23, 2016. DAL also 
asked that credit be given in paragraph (h)(1) of the proposed AD for 
previously accomplished actions using Airbus Service Bulletin A330-53-
3215, Revision 01, dated April 17, 2014. DAL stated that if the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3215, 
Revision 01, dated April 17, 2014, are used, operators may incorrectly 
reference kit part numbers in their instructions and would then need to 
submit a request for approval of an alternative method of compliance 
for the replaced part.
    We agree with the commenter's request to refer to Airbus Service 
Bulletin A330-53-3215, Revision 02, dated November 23, 2016. Airbus 
Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016, 
has also been issued. No additional work is required by Airbus Service 
Bulletins A330-53-3215, Revision 02; and A340-53-4215, Revision 02, 
both dated November 23, 2016; the revised service information merely 
corrects typographical errors and contains minor editorial changes.
    We have revised the Related Service Information under 1 CFR part 51 
section of this final rule and paragraphs (g), (g)(1), and (g)(2) of 
this AD to refer to Airbus Service Bulletin A330-53-3215, Revision 02, 
dated November 23, 2016; and Airbus Service Bulletin A340-53-4215, 
Revision 02, dated November 23, 2016. We have also revised paragraph 
(h)(1) of this AD to provide credit for actions accomplished prior to 
the effective date of this AD using Airbus Service Bulletin A330-53-
3215, Revision 01, dated April 17, 2014; and Airbus Service Bulletin 
A340-53-4215, Revision 01, dated April 17, 2014.

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 changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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 A330-53-3215, Revision 02, 
dated November 23, 2016; and Airbus Service Bulletin A340-53-4215, 
Revision 02, dated November 23, 2016. The service information describes 
procedures for repetitive rototest inspections of certain fastener 
holes, and related investigative and corrective actions if necessary. 
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 41 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                           Cost per
                Action                           Labor cost              Parts cost        product                   Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection...........................  41 work-hours x $85 per hour               $0           $3,485   $142,885 per inspection cycle.
                                        = $3,485 per inspection
                                        cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
are required based on the results of the required 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
----------------------------------------------------------------------------------------------------------------
Repair....................................  46 work-hours x $85 per hour =              $4,186           $8,096
                                             $3,910.
----------------------------------------------------------------------------------------------------------------

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 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:

[[Page 18549]]

    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):

2017-07-07 Airbus: Amendment 39-18845; Docket No. FAA-2016-9192; 
Directorate Identifier 2016-NM-038-AD.

(a) Effective Date

    This AD is effective May 25, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD, having serial 
numbers 0176 through 0915 inclusive.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracking at fastener holes 
located at frame (FR) 40 on the lower shell panel junction. We are 
issuing this AD to detect and correct cracking at FR40 on the lower 
shell panel junction; such cracking could lead to reduced structural 
integrity of the fuselage.

(f) Compliance

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

(g) Repetitive Inspections and Related Investigative and Corrective 
Actions

    Within the compliance times defined in table 1 to the 
introductory text of paragraph (g) of this AD, and, thereafter, at 
intervals not to exceed the compliance times defined in Airbus 
Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; 
or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 
23, 2016; as applicable, depending on airplane utilization and 
configuration: Accomplish a special detailed inspection of fastener 
holes located at FR40 lower shell panel junction on both left-hand 
(LH) and right-side (RH) sides, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3215, 
Revision 02, dated November 23, 2016; or Airbus Service Bulletin 
A340-53-4215, Revision 02, dated November 23, 2016; as applicable.

Table 1 to the Introductory Text of Paragraph (g) of this AD--Compliance
                       Time for Initial Inspection
------------------------------------------------------------------------
                                            Compliance time (whichever
                                              occurs later, A or B)
------------------------------------------------------------------------
A......................................  Before exceeding the compliance
                                          time ``threshold'' defined in
                                          table 1 of Airbus Service
                                          Bulletin A330-53-3215,
                                          Revision 02, dated November
                                          23, 2016; or Airbus Service
                                          Bulletin A340-53-4215,
                                          Revision 02, dated November
                                          23, 2016; as applicable,
                                          depending on airplane
                                          utilization and configuration
                                          and to be counted from
                                          airplane first flight
B......................................  For Model A330 airplanes:
                                          Within 2,400 flight cycles or
                                          24 months, whichever occurs
                                          first after the effective date
                                          of this AD
                                         For Model A340 airplanes:
                                          Within 1,300 flight cycles or
                                          24 months, whichever occurs
                                          first after the effective date
                                          of this AD
------------------------------------------------------------------------

    (1) If, during any inspection required by the introductory text 
of paragraph (g) of this AD, any crack is detected, before further 
flight, accomplish all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3215, Revision 02, 
dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, 
Revision 02, dated November 23, 2016; as applicable, except where 
Airbus Service Bulletin A330-53-3215, Revision 02, dated November 
23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, 
dated November 23, 2016, specifies to contact Airbus for repair 
instructions, and specifies that action as ``RC'' (Required for 
Compliance), this AD requires repair before further flight 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).
    (2) If, during any inspection required by the introductory text 
of paragraph (g) of this AD, the hole diameter is not within 
tolerance of the transition fit as nominal, or first oversize, or 
second oversize, or next nominal, as applicable, and Airbus Service 
Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or 
Airbus Service Bulletin A340-53-4215, Revision 02, dated November 
23, 2016, specifies to contact Airbus for repair instructions, and 
specifies that action as ``RC'' (Required for Compliance), before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.
    (3) Accomplishment of corrective actions, as required by 
paragraph (g)(1) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (g) of this AD.
    (4) Accomplishment of a repair on an airplane, as required by 
paragraph (g)(2) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (g) of this AD for that airplane, unless the method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA indicates 
otherwise.

(h) Credit for Previous Actions

    (1) This paragraph provides credit for inspections required by 
the introductory text of paragraph (g) of this AD and the related 
investigative and corrective actions required by paragraph (g)(1) of 
this AD, if those actions were performed before the effective date 
of this AD using Airbus Service Bulletin A330-53-3215, dated June 
21, 2013; or Revision 01, dated April 17, 2014; or Airbus Service 
Bulletin A340-53-4215, dated June 21, 2013; or Revision 01, dated 
April 17, 2014; as applicable.
    (2) This paragraph provides credit for the inspections and 
corrective actions required by paragraph (g) of this AD, if those 
actions were performed before the effective date of this AD using 
Airbus Technical Disposition (TD) Reference LR57D11023360, Issue B, 
dated July 12, 2011.

(i) 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 ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate

[[Page 18550]]

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 EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (g)(1) and (g)(2) 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.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0136, dated June 13, 2014, 
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-2016-9192.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (k)(3) and (k)(4) of this AD.

(k) 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 A330-53-3215, Revision 02, dated 
November 23, 2016.
    (ii) Airbus Service Bulletin A340-53-4215, Revision 02, dated 
November 23, 2016.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email [email protected]; 
Internet http://www.airbus.com.
    (4) 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.
    (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 March 28, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-06712 Filed 4-19-17; 8:45 am]
 BILLING CODE 4910-13-P

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