80 FR 67348 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 211 (November 2, 2015)

Page Range		67348-67351
FR Document		2015-27725
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.
Federal Register, Volume 80 Issue 211 (Monday, November 2, 2015)
[Federal Register Volume 80, Number 211 (Monday, November 2, 2015)]
[Proposed Rules]
[Pages 67348-67351]
From the Federal Register Online  [www.thefederalregister.org]
[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
67348

Proposed Rules Federal Register
Vol. 80, No. 211

Monday, November 2, 2015

This section of the FEDERAL REGISTER • Hand Delivery: U.S. Department of closing date and may amend this
contains notices to the public of the proposed Transportation, Docket Operations, M– proposed AD based on those comments.
issuance of rules and regulations. The 30, West Building Ground Floor, Room We will post all comments we
purpose of these notices is to give interested W12–140, 1200 New Jersey Avenue SE., receive, without change, to http://
persons an opportunity to participate in the Washington, DC, between 9 a.m. and 5 www.regulations.gov, including any
rule making prior to the adoption of the final
p.m., Monday through Friday, except personal information you provide. We
rules.
Federal holidays. will also post a report summarizing each
For service information identified in substantive verbal contact we receive
DEPARTMENT OF TRANSPORTATION this proposed AD, contact Airbus SAS, about this proposed AD.
Airworthiness Office—EAL, 1 Rond Discussion
Federal Aviation Administration Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 The European Aviation Safety Agency
14 CFR Part 39 96; fax +33 5 61 93 45 80; email (EASA), which is the Technical Agent
airworthiness.A330-A340@airbus.com; for the Member States of the European
[Docket No. FAA–2015–4808; Directorate Union, has issued EASA Airworthiness
Identifier 2014–NM–134–AD] Internet http://www.airbus.com. You
may view this referenced service Directive 2014–0149, dated June 13,
RIN 2120–AA64 information at the FAA, Transport 2014 (referred to after this as the
Airplane Directorate, 1601 Lind Avenue Mandatory Continuing Airworthiness
Airworthiness Directives; Airbus SW., Renton, WA. For information on Information, or ‘‘the MCAI’’), to correct
Airplanes the availability of this material at the an unsafe condition for certain Airbus
FAA, call 425–227–1221. Model A330–200, –200 Freighter, and
AGENCY: Federal Aviation –300 series airplanes; and Model A340–
Administration (FAA), DOT. Examining the AD Docket 200 and –300 series airplanes. The
ACTION: Notice of proposed rulemaking MCAI states:
You may examine the AD docket on
(NPRM). During accomplishment of A330
the Internet at http://
www.regulations.gov by searching for Airworthiness Limitation Item (ALI) task 57–
SUMMARY: We propose to adopt a new 11–04 on the rear fitting of the Frame (FR)
airworthiness directive (AD) for certain and locating Docket No. FAA–2015– 40 between stringers 38 and 39 on both [left-
Airbus Model A330–200, –200 4808; or in person at the Docket hand] LH/[right-hand] RH sides, cracks were
Freighter, and –300 series airplanes; and Management Facility between 9 a.m. found on an adjacent hole. After reaming at
Model A340–200 and –300 series and 5 p.m., Monday through Friday, second oversize of the subject hole, the crack
airplanes. This proposed AD was except Federal holidays. The AD docket was still present.
prompted by reports that cracks were contains this proposed AD, the Other crack findings on this adjacent hole
regulatory evaluation, any comments have been reported on A330 and A340–200/
found on an adjacent hole of certain –300 aeroplanes as a result of sampling
frames of the center wing box (CWB). received, and other information. The
inspections.
This proposed AD would require street address for the Docket Operations This condition, if not detected and
removing fasteners, a rototest inspection office (telephone 800–647–5527) is in corrected, could affect the structural integrity
of fastener holes, installing new the ADDRESSES section. Comments will of the aeroplane.
fasteners; and if necessary, oversizing be available in the AD docket shortly For the reasons described above, this
the holes and doing rototest inspections after receipt. [EASA] AD requires removal of the fasteners
and repetitive rototest inspections of fastener
for cracks, and repairing any cracking FOR FURTHER INFORMATION CONTACT: holes at FR40 vertical web located above
that is found. We are proposing this AD Vladimir Ulyanov, Aerospace Engineer, Center Wing Box (CWB) lower panel
to detect and correct cracking on certain International Branch, ANM–116, reference and/or below CWB lower panel
holes of certain frames of the CWB, Transport Airplane Directorate, FAA, reference on both sides and, depending on
which could affect the structural 1601 Lind Avenue SW., Renton, WA findings, accomplishment of the applicable
integrity of the airplane. 98057–3356; telephone 425–227–1138; corrective actions.
Note: These holes affected by this [EASA]
DATES: We must receive comments on fax 425–227–1149. AD are different from the ones affected by
this proposed AD by December 17, SUPPLEMENTARY INFORMATION: EASA AD 2009–0001 [http://
2015. ad.easa.europa.eu/blob/easa_ad_2009_
Comments Invited 0001.pdf/AD_2009-0001_1].
ADDRESSES: You may send comments,
using the procedures found in 14 CFR We invite you to send any written Required actions also include
11.43 and 11.45, by any of the following relevant data, views, or arguments about oversizing certain holes, installing new
methods: this proposed AD. Send your comments fasteners, and repairing any cracking
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS

• Federal eRulemaking Portal: Go to to an address listed under the that is found. The initial compliance
http://www.regulations.gov. Follow the ADDRESSES section. Include ‘‘Docket No. times range from 13,500 to 30,900 flight
instructions for submitting comments. FAA–2015–4808; Directorate Identifier cycles, or 57,000 to 162,000 flight hours,
• Fax: 202–493–2251. 2014–NM–134–AD’’ at the beginning of depending on operation and utilization.
• Mail: U.S. Department of your comments. We specifically invite The repetitive compliance times are
Transportation, Docket Operations, M– comments on the overall regulatory, 7,400 flight cycles/24,300 flight hours or
30, West Building Ground Floor, Room economic, environmental, and energy 5,950 flight cycles/40,400 flight hours
W12–140, 1200 New Jersey Avenue SE., aspects of this proposed AD. We will from ALI embodiment. You may
Washington, DC 20590. consider all comments received by the examine the MCAI in the AD docket on

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Federal Register / Vol. 80, No. 211 / Monday, November 2, 2015 / Proposed Rules 67349

the Internet at http:// In addition, we estimate that any The Proposed Amendment
www.regulations.gov by searching for necessary follow-on actions would take Accordingly, under the authority
and locating Docket No. FAA–2015– up to 98 work-hours and require parts delegated to me by the Administrator,
4808. costing $136,400, for a cost of up to the FAA proposes to amend 14 CFR part
$144,730 per product. We have no way 39 as follows:
Related Service Information Under 1
CFR Part 51 of determining the number of aircraft
that might need this action. PART 39—AIRWORTHINESS
Airbus has issued the following
Authority for This Rulemaking DIRECTIVES
service information. The service
information describes procedures for Title 49 of the United States Code ■ 1. The authority citation for part 39
removing the fasteners and doing a specifies the FAA’s authority to issue continues to read as follows:
repetitive rototest inspection of fastener rules on aviation safety. Subtitle I,
holes at frame (FR) 40 vertical web on Authority: 49 U.S.C. 106(g), 40113, 44701.
section 106, describes the authority of
both sides, installing new fasteners in the FAA Administrator. ‘‘Subtitle VII: § 39.13 [Amended]
transition fit, and oversizing the holes. Aviation Programs,’’ describes in more ■ 2. The FAA amends § 39.13 by adding
• Airbus Service Bulletin A330–57– detail the scope of the Agency’s the following new airworthiness
3114, dated March 12, 2013. authority.
• Airbus Service Bulletin A330–57– directive (AD):
We are issuing this rulemaking under Airbus: Docket No. FAA–2015–4808;
3115, dated April 4, 2013.
• Airbus Service Bulletin A330–57– the authority described in ‘‘Subtitle VII, Directorate Identifier 2014–NM–134–AD.
3116, dated March 12, 2013. Part A, Subpart III, Section 44701:
General requirements.’’ Under that (a) Comments Due Date
• Airbus Service Bulletin A340–57–
section, Congress charges the FAA with We must receive comments by December
4123, dated March 12, 2013.
17, 2015.
• Airbus Service Bulletin A340–57– promoting safe flight of civil aircraft in
4124, Revision 01, dated August 22, air commerce by prescribing regulations (b) Affected ADs
2013. for practices, methods, and procedures None.
• Airbus Service Bulletin A340–57– the Administrator finds necessary for
4125, dated March 12, 2013. safety in air commerce. This regulation (c) Applicability
This service information is reasonably is within the scope of that authority This AD applies to the airplanes identified
available because the interested parties because it addresses an unsafe condition in paragraphs (c)(1) and (c)(2) of this AD,
have access to it through their normal that is likely to exist or develop on certificated in any category, all manufacturer
course of business or by the means products identified in this rulemaking serial numbers, except those on which
Airbus Modification (Mod) 55792 or Mod
identified in the ADDRESSES section of action.
55306 has been embodied in production, and
this NPRM. Regulatory Findings except those on which Airbus Repair
FAA’s Determination and Requirements Instruction R57115092 has been embodied in
We determined that this proposed AD service on both right-hand (RH) and left-hand
of This Proposed AD
would not have federalism implications (LH) sides.
This product has been approved by under Executive Order 13132. This (1) Airbus Model A330–201, –202, –203,
the aviation authority of another proposed AD would not have a –223, –223F, –243 –243F, –301, –302, –303,
country, and is approved for operation substantial direct effect on the States, on –321, –322, –323, –341, –342, and –343
in the United States. Pursuant to our the relationship between the national airplanes.
bilateral agreement with the State of (2) Airbus Model A340–211, –212, –213,
Government and the States, or on the
Design Authority, we have been notified –311, –312, and –313 airplanes.
distribution of power and
of the unsafe condition described in the responsibilities among the various (d) Subject
MCAI and service information levels of government. Air Transport Association (ATA) of
referenced above. We are proposing this For the reasons discussed above, I America Code 57, Wings.
AD because we evaluated all pertinent certify this proposed regulation: (e) Reason
information and determined an unsafe 1. Is not a ‘‘significant regulatory
condition exists and is likely to exist or This AD was prompted by reports that
action’’ under Executive Order 12866; cracks were found on an adjacent hole of
develop on other products of these same
2. Is not a ‘‘significant rule’’ under the certain frames of the center wing box (CWB).
type designs.
DOT Regulatory Policies and Procedures We are issuing this AD to detect and correct
Costs of Compliance (44 FR 11034, February 26, 1979); cracking on certain holes of the CWB, which
3. Will not affect intrastate aviation in could affect the structural integrity of the
We estimate that this proposed AD airplane.
affects 35 airplanes of U.S. registry. Alaska; and
We also estimate that it would take 4. Will not have a significant (f) Compliance
about 78 work-hours per product to economic impact, positive or negative, Comply with this AD within the
comply with the basic requirements of on a substantial number of small entities compliance times specified, unless already
this proposed AD. The average labor under the criteria of the Regulatory done.
rate is $85 per work-hour. Required Flexibility Act. (g) Inspection
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS

parts would cost about $0 per product. Do a rototest inspection of the fastener
List of Subjects in 14 CFR Part 39
Based on these figures, we estimate the holes at the frame (FR) 40 vertical web, on
cost of this proposed AD on U.S. Air transportation, Aircraft, Aviation both sides, as specified in table 1 to
operators to be $232,050, or $6,630 per safety, Incorporation by reference, paragraph (g) of this AD, except as required
product, per inspection cycle. Safety. by paragraph (k) of this AD.

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67350 Federal Register / Vol. 80, No. 211 / Monday, November 2, 2015 / Proposed Rules

TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE LOCATION, METHOD, AND TIME
At the later of—
In accordance with the
For model In configuration Inspect accomplishment instruc- The applicable time speci-
tions of fied in paragraph 1.E., And the earlier of
‘‘Compliance,’’ of

A330–300 series Pre-mod 44360 .. Below the CWB Airbus Service Bulletin Airbus Service Bulletin Within 2,400 flight cycles
airplanes. lower panel A330–57–3114, dated A330–57–3114, dated or 24 months after the
reference. March 12, 2013. March 12, 2013. effective date of this
AD.
A330–200 and Post-mod 44360 Below the CWB Airbus Service Bulletin Airbus Service Bulletin Within 2,400 flight cycles
–300 series air- and pre-mod lower panel A330–57–3116, dated A330–57–3116, dated or 24 months after the
planes. 49202. reference. March 12, 2013. March 12, 2013. effective date of this
AD.
A330–200 and Pre-mod 55306 Above the CWB Airbus Service Bulletin Airbus Service Bulletin Within 2,400 flight cycles
–300 series air- and pre-mod lower panel A330–57–3115, dated A330–57–3115, dated or 24 months after the
planes. 55792. reference. April 4, 2013. April 4, 2013. effective date of this
AD.
A340–200 and Pre-mod 44360 .. Below the CWB Airbus Service Bulletin Airbus Service Bulletin Within 1,300 flight cycles
–300 series air- lower panel A340–57–4123, dated A340–57–4123, dated or 24 months after the
planes. reference. March 12, 2013. March 12, 2013. effective date of this
AD.
A340–200 and Pre-mod 55306 Above the CWB Airbus Service Bulletin Airbus Service Bulletin Within 1,300 flight cycles
–300 series air- and pre-mod lower panel A340–57–4124, Revi- A340–57–4124, Revi- or 24 months after the
planes. 55792. reference. sion 01, dated August sion 01, dated August effective date of this
22, 2013. 22, 2013. AD.
A340–200 and Post-mod 44360 Below the CWB Airbus Service Bulletin Airbus Service Bulletin Within 1,300 flight cycles
–300 series air- and pre-mod lower panel A340–57–4125, dated A340–57–4125, dated or 24 months after the
planes. 4902. reference. March 12, 2013. March 12, 2013. effective date of this
AD.

(h) Follow-On Actions: No Cracking (2) If cracking is found during the rototest (2) Where paragraph 1.E., ‘‘Compliance,’’ of
If no crack is found during any inspection inspection required by paragraph (i) of this the service information specified in table 1 to
required by paragraph (g) of this AD, do the AD, before further flight, repair using a paragraph (g) of this AD specifies a
actions specified in paragraphs (h)(1) and method approved by the Manager, Compliance Time in terms of a ‘‘Threshold’’
(h)(2) of this AD. International Branch, ANM–116, Transport and ‘‘Grace Period,’’ this AD requires
(1) Before further flight, install new Airplane Directorate, FAA; or the European compliance at the later of the applicable
fasteners in the transition fit, in accordance Aviation Safety Agency (EASA); or Airbus’s Threshold and Grace Period.
with the Accomplishment Instructions of the EASA Design Organization Approval (DOA). (3) Where paragraph 1.E., ‘‘Compliance,’’ of
service information identified in table 1 to the service information specified in table 1 to
paragraph (g) of this AD; as applicable. (j) Terminating Action Specifications
paragraph (g) of this AD specifies a
(2) Repeat the inspection required by Accomplishment of the initial and Threshold as ‘‘before next flight,’’ this AD
paragraph (g) of this AD thereafter at the repetitive inspections required by this AD requires compliance before the next flight
applicable time identified in paragraph 1.E., terminates accomplishment of Airworthiness after the applicable finding.
‘‘COMPLIANCE,’’ of the service information Limitation Items Tasks 57–11–04 and 57–11–
identified in table 1 to paragraph (g) of this 02 of the Airworthiness Limitation Section (l) Credit for Previous Actions
AD; as applicable. (ALS) Part 2, Damage Tolerant Airworthiness This paragraph provides credit for actions
(i) Follow-On Actions for Crack Findings Limitation Items (DT ALI). required by paragraphs (g) and (i) of this AD,
(1) Installation of new fasteners as if those actions were performed before the
If any crack is found during any inspection specified in paragraph (h)(1) of this AD does effective date of this AD using the service
required by paragraph (g) of this AD: Before information specified in paragraph (l)(1),
not terminate the repetitive inspections
further flight, oversize the holes to the first (l)(2), (l)(3), (l)(4), (l)(5), (l)(6), (l)(7), (l)(8), or
required by paragraph (g) of this AD.
oversize in comparison with the current hole (l)(9) of this AD. This service information is
diameter, and do a rototest inspection for (2) Accomplishment of the corrective
actions specified in paragraphs (i) and (i)(1) not incorporated by reference in this AD.
cracks, in accordance with the
of this AD does not terminate the repetitive (1) Airbus Technical Disposition Reference
Accomplishment Instructions of the service
inspections required by paragraph (g) of this LR57D11023270, Issue B, dated July 12,
information identified in table 1 to paragraph
(g) of this AD; as applicable. AD. 2011.
(1) If no cracking is found during the (3) Accomplishment of the repair specified (2) Airbus Technical Disposition Reference
rototest inspection required by paragraph (i) in paragraph (i)(2) of this AD does not LR57D11029171, Issue B, dated September 6,
of this AD, do the actions specified in terminate repetitive inspections required by 2011.
paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. paragraph (g) of this AD, unless the approved (3) Airbus Technical Disposition Reference
(i) Before further flight: Install new repair method specified otherwise. LR57D11029173, Issue B, dated September 6,
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS

fasteners in the transition fit, in accordance 2011.
(k) Exceptions to Service Information (4) Airbus Technical Disposition Reference
with the Accomplishment Instructions of the
service information identified in table 1 to (1) If the service information identified in LR57D11030741, Issue B, dated September
paragraph (g) of this AD; as applicable. table 1 to paragraph (g) of this AD specifies 22, 2011.
(ii) Repeat the inspection required by contacting Airbus for appropriate action: (5) Airbus Technical Disposition Reference
paragraph (g) of this AD thereafter at the Before further flight, repair using a method LR57D11029170, Issue C, dated September 6,
applicable time identified in paragraph 1.E., approved by the Manager, International 2011.
‘‘COMPLIANCE,’’ of the service information Branch, ANM–116, Transport Airplane (6) Airbus Technical Disposition Reference
identified in table 1 to paragraph (g) of this Directorate, FAA; or the EASA; or Airbus’s LR57D11023714, Issue B, dated July 12,
AD; as applicable. EASA DOA. 2011.

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Document Created: 2018-03-01 11:30:10
Document Modified: 2018-03-01 11:30:10
Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by December 17, 2015.
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.
FR Citation		80 FR 67348
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
80 FR 67348 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 211 (November 2, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
