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[Federal Register Volume 79, Number 248 (Monday, December 29, 2014)]
[Proposed Rules]
[Pages 77972-77975]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-30270]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-040-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-
300, A340-500, and A340-600 series airplanes. This proposed AD was 
prompted by a report of skin disbonding on a composite side panel of a 
rudder installed on an A310 airplane. This proposed AD would require a 
review of the maintenance records of the rudder to determine if any 
composite side shell panel repair has been done; a thermography 
inspection limited to the repair areas or complete side shells, as 
applicable, to identify possible in-service rudder repairs, damages, or 
fluid ingress; and applicable related investigative and corrective 
actions. We are proposing this AD to detect and correct the rudder skin 
disbonding, which could affect the structural integrity of the rudder, 
and could result in reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by February 12, 
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

[[Page 77973]]

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. 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-2014-
0928; 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-2014-0928; 
Directorate Identifier 2014-NM-040-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 Community, has issued EASA 
Airworthiness Directive 2014-0033, dated February 4, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, 
and A340-600 series airplanes. The MCAI states:

    A case of skin disbonding was reported on a composite side panel 
of a rudder installed on an A310 aeroplane.
    The investigation results revealed that this disbonding started 
from a skin panel area previously repaired in-service in accordance 
with the Structural Repair Manual (SRM).
    The initial damage has been identified as a disbonding between 
the core and skin of the repaired area. This damage may not be 
visually detectable and likely propagates during normal operation 
due to the variation of pressure during ground-air-ground cycles.
    Composite rudder side shell panels are also installed on A330 
and A340 aeroplanes, which may have been repaired in-service using a 
similar method.
    This condition, if not detected and corrected, could affect the 
structural integrity of the rudder, possibly resulting in reduced 
control of the aeroplane.
    For the reasons described above, this [EASA] AD requires a one-
time thermography inspection of a repaired rudder or a rudder whose 
maintenance records are incomplete and, depending on findings, 
accomplishment of applicable corrective and follow-up actions 
[including repetitive inspections.

    The related investigative actions in this AD include, as 
applicable, an ultrasonic inspection, an elasticity laminate checker 
inspection, a tap test inspection, detailed inspections, thermography 
inspections, and ventilation of the core. The repetitive inspections 
include detailed inspections and thermography inspections. The 
corrective actions in this AD include repairs.
    The compliance time for the related investigative actions is before 
further flight after accomplishing the applicable inspection required 
by paragraph (g)(1) or (g)(2)(ii) of this AD.
    The intervals for the repetitive inspections are either 900 flight 
hours or 1,000 flight cycles, depending on the applicable conditions 
identified in the service information.
    The compliance times for the corrective actions range, depending on 
the applicable conditions identified in the service information, from 
before further flight to within 4,500 flight cycles but not to exceed 
24 months after accomplishing the applicable inspection required by 
paragraphs (g)(1) or (g)(2)(ii) of this AD.
    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-2014-
0928.

Relevant Service Information

    Airbus has issued the following service information:
     Airbus Service Bulletin A330-55-3043, dated February 7, 
2013.
     Airbus Service Bulletin A340-55-4039, dated February 7, 
2013.
     Airbus Service Bulletin A340-55-5007, dated February 7, 
2013.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

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 55 airplanes of U.S. 
registry.
    We also estimate that it would take about 45 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 $210,375, or $3,825 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed

[[Page 77974]]

AD is mandatory. Comments concerning the accuracy of this burden and 
suggestions for reducing the burden should be directed to the FAA at 
800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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. Amend Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-
040-AD.

(a) Comments Due Date

    We must receive comments by February 12, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, 
all manufacturer serial numbers.
    (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, 
and -642 airplanes, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Reason

    This AD was prompted by a report of skin disbonding on a 
composite side panel of a rudder installed on an A310 airplane. We 
are issuing this AD to detect and correct the rudder skin 
disbonding, which could affect the structural integrity of the 
rudder, and could result in reduced controllability of the airplane.

(f) Compliance

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

(g) Review the Maintenance Records

    Within 24 months after the effective date of this AD: Review the 
maintenance records of the rudder to determine if any composite side 
shell panel repair has been accomplished on the rudder since first 
installation on an airplane.
    (1) If, based on the maintenance record review, any repair 
identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA 
(Sheet 02) of the service information specified in paragraphs 
(g)(1)(i) through (g)(1)(iii) of this AD is found: Within 24 months 
after the effective date of this AD, do a thermography inspection 
for repair, damages, and fluid ingress, limited to the repaired 
areas, in accordance with the Accomplishment Instructions of the 
applicable service information specified in paragraphs (g)(1)(i) 
through (g)(1)(iii) of this AD:
    (i) Airbus Service Bulletin A330-55-3043, dated February 7, 2013 
(for Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -
302, -303, -321, -322, -323, -341, -342, and -343 airplanes).
    (ii) Airbus Service Bulletin A340-55-4039, dated February 7, 
2013 (for Model A340-211, -212, -213, -311, -312, and -313 
airplanes).
    (iii) Airbus Service Bulletin A340-55-5007, dated February 7, 
2013 (for Model A340-541 and -642 airplanes).
    (2) For a rudder for which maintenance records are unavailable 
or incomplete, do the actions specified in paragraph (g)(2)(i) and 
(g)(2)(ii) of this AD:
    (i) No later than 3 months before accomplishment of the 
thermography inspection, as required by paragraph (g)(2)(ii) of this 
AD, contact Airbus to request related rudder manufacturing reworked 
data by submitting the serial number of the rudder to Airbus.
    (ii) Within 24 months after the effective date of this AD: Do a 
thermography inspection for any repair on complete side shells to 
identify and mark any repair, in accordance with the Accomplishment 
Instructions of the applicable service information specified in 
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD.

(h) Related Investigative Actions, Corrective Actions, and Repetitive 
Inspections

    After the inspection as required by paragraph (g)(1) or (g)(2) 
of this AD: At the applicable compliance times specified in 
paragraph 1.E., ``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5 
of the applicable service information specified in paragraphs 
(g)(1)(i) through (g)(1)(iii) of this AD, accomplish all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD; 
except as provided by paragraphs (i)(1) and (i)(2) of this AD. 
Options provided in the service information specified in paragraphs 
(g)(1)(i) through (g)(1)(iii) of this AD for accomplishing the 
actions are acceptable for the corresponding requirements of this 
paragraph provided that the related investigative and corrective 
actions are done at the applicable times specified in paragraph 
1.E., ``Compliance,'' of the applicable service information 
specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, 
including applicable repetitive inspection intervals. Thereafter 
repeat the inspections of the restored and repaired areas at the 
applicable compliance time specified in paragraph 1.E., 
``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5 of the applicable 
service information specified in paragraphs (g)(1)(i) through 
(g)(1)(iii) of this AD.

(i) Exceptions to the Service Information

    (1) Where the applicable service information specified in 
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD specifies a 
compliance time relative to the date of the service information, 
this AD requires compliance within the specified compliance time 
after the effective date of this AD.
    (2) If the service information in paragraphs (g)(1)(i) through 
(g)(1)(iii) of this AD specifies to contact Airbus: At the 
applicable

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compliance times specified in paragraph 1.E., ``Compliance,'' of the 
applicable service information specified in paragraphs (g)(1)(i) 
through (g)(1)(iii) of this AD, 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) Provisions for Certain Airplanes

    Airplanes fitted with a rudder having a serial number (S/N) that 
is not in the range of S/N TS-1001 through S/N TS-1043 inclusive, S/
N TS-2001 through S/N TS-2074 inclusive, S/N TS-3000 through S/N TS-
3525 inclusive, S/N TS-4001 through S/N TS-4170 inclusive, S/N TS-
6001 through S/N TS-6246 inclusive, or S/N TS-5001 through S/N TS-
5138 inclusive, are not affected by the requirements of paragraphs 
(g) and (h) of this AD provided that it is determined that no repair 
has been accomplished on the composite side shell panel of that 
rudder since first installation on the airplane.

(k) Parts Installation Limitations

    As of the effective date of this AD, no person may install, on 
any airplane, a rudder, unless the record review and thermography 
inspection specified in paragraph (g) of this AD has been done on 
that rudder and thereafter all applicable related investigative 
actions, repetitive inspections, and corrective actions are done as 
required by paragraph (h) of this AD, except as provided in 
paragraph (j) of this AD.

(l) Repair Prohibition

    As of the effective date of this AD, no person may accomplish a 
side shell repair on any rudder using a structure repair manual 
procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure 
A-GBCAA (Sheet 02) of the service information specified in 
paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable, 
on any airplane.

(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.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0033, dated February 4, 
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-2014-0928.
    (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 airworthiness.A330-A340@airbus.com; 
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 December 17, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-30270 Filed 12-24-14; 8:45 am]
BILLING CODE 4910-13-P
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