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[Federal Register Volume 81, Number 89 (Monday, May 9, 2016)]
[Rules and Regulations]
[Pages 27986-27989]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-10287]

[[Page 27986]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4808; Directorate Identifier 2014-NM-134-AD; 
Amendment 39-18509; AD 2016-09-11]
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 A330-200, -200 Freighter, and -300 series airplanes; and 
Model A340-200 and -300 series airplanes. This AD was prompted by 
reports that cracks were found on an adjacent hole of certain frames of 
the center wing box (CWB). This AD requires removing fasteners, doing a 
rototest inspection of fastener holes, installing new fasteners, 
oversizing the holes and doing rototest inspections for cracks if 
necessary, and repairing any cracking that is found. We are issuing 
this AD to detect and correct cracking on certain holes of certain 
frames of the CWB that could affect the structural integrity of the 
airplane.

DATES: This AD becomes effective June 13, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 13, 
2016.

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 airworthiness.A330-A340@airbus.com; Internet 
http://www.airbus.com. 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-2015-4808.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-4808; 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 Operations 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.

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, -200 Freighter, and -300 series airplanes; and Model A340-200 and 
-300 series airplanes. The NPRM published in the Federal Register on 
November 2, 2015 (80 FR 67348) (``the NPRM''). We are issuing this AD 
to detect and correct cracking on certain holes of certain frames of 
the CWB, which could affect the 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 
Airworthiness Directive 2014-0149, 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 
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 
and -300 series airplanes. The MCAI states:

    During accomplishment of A330 Airworthiness Limitation Item 
(ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between 
stringers 38 and 39 on both [left-hand] LH/[right-hand] RH sides, 
cracks were found on an adjacent hole. After reaming at second 
oversize of the subject hole, the crack was still present.
    Other crack findings on this adjacent hole have been reported on 
A330 and A340-200/300 aeroplanes as a result of sampling 
inspections.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    For the reasons described above, this [EASA] AD requires removal 
of the fasteners and repetitive rototest inspections of fastener 
holes at FR40 vertical web located above Center Wing Box (CWB) lower 
panel reference and/or below CWB lower panel reference on both sides 
and, depending on findings, accomplishment of the applicable 
corrective actions.
    Note: These holes affected by this [EASA] AD are different from 
the ones affected by EASA AD 2009-0001 [http://ad.easa.europa.eu/blob/easa_ad_2009_0001.pdf/AD_2009-0001_1].

    Required actions also include oversizing certain holes, installing 
new fasteners, and repairing any cracking that is found. The initial 
compliance times range from 13,500 to 30,900 flight cycles, or 57,000 
to 162,000 flight hours, depending on airplane operation and 
utilization. The repetitive compliance times are 7,400 flight cycles/
24,300 flight hours or 5,950 flight cycles/40,400 flight hours from ALI 
embodiment. 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-2015-4808.

Change Made to the Format of Paragraph (g) of This AD

    At the request of the Office of the Federal Register, we have 
revised the format of paragraph (g) of this AD by converting the table 
to text. This change to the format does not affect the requirements of 
that paragraph.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter, Bowen Gass, 
supported the NPRM.

Conclusion

    We reviewed the relevant data, considered the comment received, 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 the following service information. The service 
information describes procedures for removing the fasteners and doing a 
repetitive rototest inspection of fastener holes at FR40 vertical web 
on both sides, installing new fasteners in transition fit, and 
oversizing the holes.
     Airbus Service Bulletin A330-57-3114, dated March 12, 
2013.
     Airbus Service Bulletin A330-57-3115, dated April 4, 2013.

[[Page 27987]]

     Airbus Service Bulletin A330-57-3116, dated March 12, 
2013.
     Airbus Service Bulletin A340-57-4123, dated March 12, 
2013.
     Airbus Service Bulletin A340-57-4124, Revision 01, dated 
August 22, 2013.
     Airbus Service Bulletin A340-57-4125, dated March 12, 
2013.
    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 35 airplanes of U.S. registry.
    We also estimate that it will take about 78 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $0 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $232,050, per inspection cycle, or $6,630 per 
product, per inspection cycle.
    In addition, we estimate that any necessary follow-on actions will 
take about 98 work-hours and require parts costing $136,400, for a cost 
of up to $144,730 per product. We have no way of determining the number 
of aircraft that might need this action.

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:
    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):

2016-09-11 Airbus: Amendment 39-18509. Docket No. FAA-2015-4808; 
Directorate Identifier 2014-NM-134-AD.

(a) Effective Date

    This AD becomes effective June 13, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers, except those on which Airbus 
Modification (Mod) 55792 or Mod 55306 has been embodied in 
production, and except those on which Airbus Repair Instruction 
R57115092 has been embodied in service on both right-hand (RH) and 
left-hand (LH) sides.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243 -243F, 
-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 57, Wings.

(e) Reason

    This AD was prompted by reports that cracks were found on an 
adjacent hole of certain frames of the center wing box (CWB). We are 
issuing this AD to detect and correct cracking on certain holes of 
the CWB, which could affect the structural integrity of the 
airplane.

(f) Compliance

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

(g) Inspection

    Do a rototest inspection of the fastener holes at the frame (FR) 
40 vertical web, on both sides, as specified in paragraphs (g)(1) 
through (g)(6) of this AD, except as required by paragraph (k) of 
this AD.
    (1) For Model A330-300 series airplanes in pre-mod 44360 
configuration: At the later of the times specified in paragraphs 
(g)(1)(i) and (g)(1)(ii) of this AD, inspect below the CWB lower 
panel reference, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A330-57-3114, dated March 12, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance'' of Airbus Service Bulletin A330-57-3114, dated March 
12, 2013.
    (ii) Within 2,400 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (2) For Model A330-200 series airplanes in post-mod 44360 and 
pre-mod 49202 configuration: At the later of the times specified in 
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, inspect below the 
CWB lower panel reference, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-57-3116, dated March 
12, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A330-57-3116, dated March 
12, 2013.
    (ii) Within 2,400 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (3) For Model A330-200 and -300 series airplanes in pre-mod 
55306 and pre-mod 55792 configuration: At the later of the times 
specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD, inspect 
above the CWB lower panel reference, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-57-3115, 
dated April 4, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance'' of Airbus Service Bulletin A330-57-3115, dated April 
4, 2013.
    (ii) Within 2,400 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (4) For Model A340-200 and -300 series airplanes in pre-mod 
44360 configuration: At the later of the times specified in 
paragraphs (g)(4)(i) and (g)(4)(ii) of this AD, inspect below the 
CWB lower panel reference, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A340-57-4123, dated March 
12, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance'' of Airbus

[[Page 27988]]

Service Bulletin A330-57-4123, dated March 12, 2013.
    (ii) Within 1,300 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (5) For Model A340-200 and -300 series airplanes in pre-mod 
55306 and pre-mod 55792 configuration: At the later of the times 
specified in paragraphs (g)(5)(i) and (g)(5)(ii) of this AD, inspect 
above the CWB lower panel reference, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-57-4124, 
Revision 01, dated August 22, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A340-57-4124, Revision 
01, dated August 22, 2013.
    (ii) Within 1,300 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.
    (6) For Model A340-200 and -300 series airplanes in post-mod 
44360 and pre-mod 49202 configuration: At the later of the times 
specified in paragraphs (g)(6)(i) and (g)(6)(ii) of this AD, inspect 
below the CWB lower panel reference, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A340-57-4125, 
dated March 12, 2013.
    (i) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Airbus Service Bulletin A340-57-4125, dated March 
12, 2013.
    (ii) Within 1,300 flight cycles or 24 months after the effective 
date of this AD, whichever occurs first.

(h) Follow-on Actions: No Cracking

    If no crack is found during any inspection required by paragraph 
(g) of this AD, do the actions specified in paragraphs (h)(1) and 
(h)(2) of this AD.
    (1) Before further flight, install new fasteners in the 
transition fit, in accordance with the Accomplishment Instructions 
of the applicable service information identified in paragraph (g) of 
this AD.
    (2) Repeat the inspection required by paragraph (g) of this AD 
thereafter at the applicable time identified in paragraph 1.E., 
``Compliance,'' of the applicable service information identified in 
paragraph (g) of this AD.

(i) Follow-on Actions for Crack Findings

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, oversize the holes 
to the first oversize in comparison with the current hole diameter, 
and do a rototest inspection for cracks, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (g) of this AD.
    (1) If no cracking is found during the rototest inspection 
required by paragraph (i) of this AD, do the actions specified in 
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD.
    (i) Before further flight: Install new fasteners in the 
transition fit, in accordance with the Accomplishment Instructions 
of the applicable service information identified in paragraph (g) of 
this AD.
    (ii) Repeat the inspection required by paragraph (g) of this AD 
thereafter at the applicable time identified in paragraph 1.E., 
``Compliance,'' of the applicable service information identified in 
paragraph (g) of this AD.
    (2) If cracking is found during the rototest inspection required 
by paragraph (i) of this AD: Before further flight, repair 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).

(j) Terminating Action Specifications

    Accomplishment of the initial and repetitive inspections 
required by this AD terminates accomplishment of Airworthiness 
Limitation Items Tasks 57-11-04 and 57-11-02 of the Airworthiness 
Limitation Section (ALS) Part 2, Damage Tolerant Airworthiness 
Limitation Items (DT ALI).
    (1) Installation of new fasteners, as specified in paragraph 
(h)(1) of this AD, does not terminate the repetitive inspections 
required by paragraph (g) of this AD.
    (2) Accomplishment of the corrective actions specified in the 
introductory text of paragraph (i) and paragraph (i)(1) of this AD 
does not terminate the repetitive inspections required by paragraph 
(g) of this AD.
    (3) Accomplishment of the repair specified in paragraph (i)(2) 
of this AD does not terminate repetitive inspections required by 
paragraph (g) of this AD, unless the approved repair method 
specifies otherwise.

(k) Exceptions to Service Information

    (1) If the applicable service information identified in 
paragraph (g) of this AD specifies contacting Airbus for appropriate 
action: Before further flight, repair using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the EASA; or Airbus's EASA DOA.
    (2) Where paragraph 1.E., ``Compliance,'' of the applicable 
service information specified in paragraph (g) of this AD specifies 
a compliance time in terms of a ``Threshold'' and ``Grace Period,'' 
this AD requires compliance at the later of the applicable threshold 
and grace period.
    (3) Where paragraph 1.E., ``Compliance,'' of the applicable 
service information specified in paragraph (g) of this AD specifies 
a threshold as ``before next flight,'' this AD requires compliance 
before the next flight after the applicable finding.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (i) of this AD, if those actions were performed 
before the effective date of this AD using the applicable service 
information specified in paragraph (l)(1), (l)(2), (l)(3), (l)(4), 
(l)(5), (l)(6), (l)(7), (l)(8), or (l)(9) of this AD. This service 
information is not incorporated by reference in this AD.
    (1) Airbus Technical Disposition LR57D11023270, Issue B, dated 
July 12, 2011.
    (2) Airbus Technical Disposition LR57D11029171, Issue B, dated 
September 6, 2011.
    (3) Airbus Technical Disposition LR57D11029173, Issue B, dated 
September 6, 2011.
    (4) Airbus Technical Disposition LR57D11030741, Issue B, dated 
September 22, 2011.
    (5) Airbus Technical Disposition LR57D11029170, Issue C, dated 
September 6, 2011.
    (6) Airbus Technical Disposition LR57D11023714, Issue B, dated 
July 12, 2011.
    (7) Airbus Technical Disposition LR57D11029172, Issue B, dated 
September 6, 2011.
    (8) Airbus Technical Disposition LR57D11030740, Issue C, dated 
September 22, 2011.
    (9) Airbus Service Bulletin A340-57-4124, dated April 4, 2013.

(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 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: 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. The 
AMOC approval letter must specifically reference this AD.
    (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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0149, 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-2015-4808.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(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

[[Page 27989]]

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 A330-57-3114, dated March 12, 2013.
    (ii) Airbus Service Bulletin A330-57-3115, dated April 4, 2013.
    (iii) Airbus Service Bulletin A330-57-3116, dated March 12, 
2013.
    (iv) Airbus Service Bulletin A340-57-4123, dated March 12, 2013.
    (v) Airbus Service Bulletin A340-57-4124, Revision 01, dated 
August 22, 2013.
    (vi) Airbus Service Bulletin A340-57-4125, dated March 12, 2013.
    (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 airworthiness.A330-A340@airbus.com; 
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 April 21, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-10287 Filed 5-6-16; 8:45 am]
 BILLING CODE 4910-13-P
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