[Federal Register Volume 80, Number 211 (Monday, November 2, 2015)]
[Proposed Rules]
[Pages 67348-67351]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27725]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 80, No. 211 / Monday, November 2, 2015 / 
Proposed Rules  

[[Page 67348]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4808; Directorate Identifier 2014-NM-134-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt 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 proposed 
AD was prompted by reports that cracks were found on an adjacent hole 
of certain frames of the center wing box (CWB). This proposed AD would 
require removing fasteners, a rototest inspection of fastener holes, 
installing new fasteners; and if necessary, oversizing the holes and 
doing rototest inspections for cracks, and repairing any cracking that 
is found. We are proposing 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.

DATES: We must receive comments on this proposed AD by December 17, 
2015.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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. 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-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 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: 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: 

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-2015-4808; 
Directorate Identifier 2014-NM-134-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 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 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

[[Page 67349]]

the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-4808.

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 frame (FR) 40 
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.
     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 of this 
NPRM.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 35 airplanes of U.S. 
registry.
    We also estimate that it would take about 78 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $232,050, or $6,630 per product, per 
inspection cycle.
    In addition, we estimate that any necessary follow-on actions would 
take up to 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2015-4808; Directorate Identifier 2014-NM-
134-AD.

(a) Comments Due Date

    We must receive comments by December 17, 2015.

(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 table 1 to paragraph 
(g) of this AD, except as required by paragraph (k) of this AD.

[[Page 67350]]



                                       Table 1 to paragraph (g) of this AD--Compliance Location, Method, and Time
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          At the later of--
                                                                                                           ---------------------------------------------
                                                                                       In accordance with    The applicable time
             For model                  In configuration             Inspect           the accomplishment        specified in
                                                                                        instructions of        paragraph 1.E.,       And the earlier of
                                                                                                              ``Compliance,'' of
--------------------------------------------------------------------------------------------------------------------------------------------------------
A330-300 series airplanes..........  Pre-mod 44360.........  Below the CWB lower     Airbus Service         Airbus Service         Within 2,400 flight
                                                              panel reference.        Bulletin A330-57-      Bulletin A330-57-      cycles or 24 months
                                                                                      3114, dated March      3114, dated March      after the effective
                                                                                      12, 2013.              12, 2013.              date of this AD.
A330-200 and -300 series airplanes.  Post-mod 44360 and pre- Below the CWB lower     Airbus Service         Airbus Service         Within 2,400 flight
                                      mod 49202.              panel reference.        Bulletin A330-57-      Bulletin A330-57-      cycles or 24 months
                                                                                      3116, dated March      3116, dated March      after the effective
                                                                                      12, 2013.              12, 2013.              date of this AD.
A330-200 and -300 series airplanes.  Pre-mod 55306 and pre-  Above the CWB lower     Airbus Service         Airbus Service         Within 2,400 flight
                                      mod 55792.              panel reference.        Bulletin A330-57-      Bulletin A330-57-      cycles or 24 months
                                                                                      3115, dated April 4,   3115, dated April 4,   after the effective
                                                                                      2013.                  2013.                  date of this AD.
A340-200 and -300 series airplanes.  Pre-mod 44360.........  Below the CWB lower     Airbus Service         Airbus Service         Within 1,300 flight
                                                              panel reference.        Bulletin A340-57-      Bulletin A340-57-      cycles or 24 months
                                                                                      4123, dated March      4123, dated March      after the effective
                                                                                      12, 2013.              12, 2013.              date of this AD.
A340-200 and -300 series airplanes.  Pre-mod 55306 and pre-  Above the CWB lower     Airbus Service         Airbus Service         Within 1,300 flight
                                      mod 55792.              panel reference.        Bulletin A340-57-      Bulletin A340-57-      cycles or 24 months
                                                                                      4124, Revision 01,     4124, Revision 01,     after the effective
                                                                                      dated August 22,       dated August 22,       date of this AD.
                                                                                      2013.                  2013.
A340-200 and -300 series airplanes.  Post-mod 44360 and pre- Below the CWB lower     Airbus Service         Airbus Service         Within 1,300 flight
                                      mod 4902.               panel reference.        Bulletin A340-57-      Bulletin A340-57-      cycles or 24 months
                                                                                      4125, dated March      4125, dated March      after the effective
                                                                                      12, 2013.              12, 2013.              date of this AD.
--------------------------------------------------------------------------------------------------------------------------------------------------------

(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 service information identified in table 1 to paragraph (g) of 
this AD; as applicable.
    (2) Repeat the inspection required by paragraph (g) of this AD 
thereafter at the applicable time identified in paragraph 1.E., 
``COMPLIANCE,'' of the service information identified in table 1 to 
paragraph (g) of this AD; as applicable.

(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 service information identified in 
table 1 to paragraph (g) of this AD; as applicable.
    (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 service information identified in table 1 to paragraph (g) of 
this AD; as applicable.
    (ii) Repeat the inspection required by paragraph (g) of this AD 
thereafter at the applicable time identified in paragraph 1.E., 
``COMPLIANCE,'' of the service information identified in table 1 to 
paragraph (g) of this AD; as applicable.
    (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 
paragraphs (i) and (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 
specified otherwise.

(k) Exceptions to Service Information

    (1) If the service information identified in table 1 to 
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 service 
information specified in table 1 to 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 service 
information specified in table 1 to 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 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 Reference LR57D11023270, Issue 
B, dated July 12, 2011.
    (2) Airbus Technical Disposition Reference LR57D11029171, Issue 
B, dated September 6, 2011.
    (3) Airbus Technical Disposition Reference LR57D11029173, Issue 
B, dated September 6, 2011.
    (4) Airbus Technical Disposition Reference LR57D11030741, Issue 
B, dated September 22, 2011.
    (5) Airbus Technical Disposition Reference LR57D11029170, Issue 
C, dated September 6, 2011.
    (6) Airbus Technical Disposition Reference LR57D11023714, Issue 
B, dated July 12, 2011.

[[Page 67351]]

    (7) Airbus Technical Disposition Reference LR57D11029172, Issue 
B, dated September 6, 2011.
    (8) Airbus Technical Disposition Reference 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: [email protected]. 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 Design Organization Approval (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) 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. 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 October 21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27725 Filed 10-30-15; 8:45 am]
 BILLING CODE 4910-13-P