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[Federal Register Volume 79, Number 40 (Friday, February 28, 2014)]
[Proposed Rules]
[Pages 11355-11358]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04495]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0123; Directorate Identifier 2013-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 
certain Airbus Model A300 B4-601, B4-603, B4-620, B4-622, -B4-605R, B4-
622R, -F4-605R, F4-622R, and -C4-605R Variant F airplanes; and Model 
A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. This 
proposed AD was prompted by a report of inner skin disbonding damage on 
a rudder. This proposed AD would require repetitive ultrasonic 
inspections for disbonding of certain rudders; an elasticity of 
laminate checker inspection; a woodpecker or tap test inspection; 
venting the core, if necessary; and repairing, if necessary. We are 
proposing this AD to detect and correct rudder disbonding, which could 
affect the structural integrity of the rudder.

DATES: We must receive comments on this proposed AD by April 14, 2014.

ADDRESSES: You may send comments 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,

[[Page 11356]]

Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email account.airworth-eas@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-
0123; or in person at the Docket Operations office 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-2125; 
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-2014-0123; 
Directorate Identifier 2013-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 2013-0039, dated February 26, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    One A310 operator found substantial inner skin disbonding damage 
on a rudder that was previously inspected in accordance with the 
instructions of Airbus Service Bulletin (SB) A310-55-2044. The 
results of the subsequent investigation revealed that the most 
probable cause of this damage was a blunt impact with no visible 
damage from outside during the rudder handling. Damage like this 
might grow with pressure variation during ground-air-ground cycles, 
and tests performed with other rudders showed a rapid propagation of 
damage during artificial pressure cycling.
    This condition, if not detected and corrected, could affect the 
structural integrity of the rudder.
    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A55W002-12 [dated December 13, 2012], 
pending Aircraft Maintenance Manual (AMM) 27-21-21 PB401 revision to 
update rudder handling procedures.
    For the reasons described above, this [EASA] AD requires 
ultrasonic test (UT) inspections of the affected rudders to detect 
signs of disbonding and, depending on findings, accomplishment of 
applicable corrective action(s).

Required actions also include an elasticity of laminate checker 
inspection to detect external and internal disbonding, and a woodpecker 
or tap test inspection to detect external disbonding. 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-* * *.

Relevant Service Information

    Airbus has issued Alert Operators Transmission A55W002-12, dated 
December 13, 2012. 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 the same 
type design.

Repair Approvals

    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the FAA AD a 
requirement to accomplish the action using a method approved by either 
the FAA or the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or DAH repair approval 
statements that were not specifically developed to address the unsafe 
condition corrected by the AD. Using repair instructions that were not 
specifically approved for a particular AD creates the potential for 
doing repairs that were not developed to address the unsafe condition 
identified by the MCAI AD, the FAA AD, or the applicable service 
information, which could result in the unsafe condition not being fully 
corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, certain requirements of this proposed 
AD specify that the repair approval specifically refer to the FAA AD. 
This change is intended to clarify the method of compliance and to 
provide operators with better visibility of repairs that are 
specifically developed and approved to correct the unsafe condition. In 
addition, we use the phrase ``its delegated agent, or the DAH with the 
State of Design Authority's design organization approval, as 
applicable'' in this proposed AD to refer to a DAH authorized to 
approve certain required repairs for this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 89 airplanes of U.S. 
registry. We also estimate that it would take about 10 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 $75,650, or $850 per product.

[[Page 11357]]

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this proposed 
AD.

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 AD:

Airbus: Docket No. FAA-2014-0123; Directorate Identifier 2013-NM-
040-AD.

(a) Comments Due Date

    We must receive comments by April 14, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, except airplanes on which modification 08827 
has been embodied in production.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, -B4-605R, 
B4-622R, -F4-605R, F4-622R, and -C4-605R Variant F airplanes, 
certificated in any category, all manufacturer serial numbers.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes, certificated in any category, 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 inner skin disbonding damage 
on a rudder. We are issuing this AD to detect and correct rudder 
disbonding, which could affect the structural integrity of the 
rudder.

(f) Compliance

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

(g) Identification of Part Number

    Within 3 months after the effective date of this AD, identify 
the rudder assembly part number (P/N) and serial number (S/N), in 
accordance with the Accomplishment Instructions of Airbus Alert 
Operator Transmission (AOT) A55W002-12, dated December 13, 2012. If 
the part number or serial number cannot be determined, before 
further flight, identify the part number and serial number in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA (or its delegated agent, or by the Design Approval Holder 
with EASA design organization approval, as applicable). For an 
identification method to be approved, the identification method 
approval must specifically refer to this AD.

(h) Inspections

    If a rudder assembly part number starting with A55471500 is 
found during the inspection required by paragraph (g) of this AD, 
before further flight, do an ultrasonic (UT) inspection for damage 
(e.g., disbonding and liquid ingress) of the rudder side panel along 
the Z-profile and in the booster area, in accordance with Airbus 
Alert Operator Transmission (AOT) A55W002-12, dated December 13, 
2012. If any damage is found, before further flight, do the 
inspections to confirm disbonding damage as specified in paragraph 
(h)(1) and (h)(2) of this AD, in accordance with Airbus Alert 
Operator Transmission (AOT) A55W002-12, dated December 13, 2012.
    (1) Do an elasticity of laminate checker inspection to detect 
external and internal disbonding of the rudder side panel along the 
Z-profile and in the booster area.
    (2) Do a woodpecker or tap test inspection to detect external 
disbonding of the rudder side panel along the Z-profile and in the 
booster area.

(i) Repair

    (1) If any disbonding is confirmed during any inspection 
required by paragraphs (h)(1) and (h)(2) of this AD, before further 
flight, repair as specified in paragraphs (i)(1)(i) and (i)(1)(ii) 
of this AD, as applicable.
    (i) If disbonding is less than or equal to 50 millimeters (mm) 
in width and less than or equal to 150 mm in length, before further 
flight, vent the core, using a method approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA (or its delegated agent, or by the Design 
Approval Holder with EASA design organization approval, as 
applicable). Within 100 flight cycles after the UT inspection 
specified in paragraph (h) of this AD is done, repair using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA (or its delegated agent, or the 
Design Approval Holder with EASA's design organization approval, as 
applicable). For a repair method to be approved, the repair approval 
must specifically refer to this AD.
    (ii) If disbonding is greater than 50 mm in width or greater 
than 150 mm in length, before further flight, repair using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA (or its delegated agent, or the 
Design Approval Holder with EASA's design organization approval, as 
applicable). For a repair method to be approved, the repair approval 
must specifically refer to this AD.
    (2) If liquid ingress is confirmed during any inspection 
required by paragraphs (h)(1) and (h)(2), before further flight, 
repair, using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or 
its delegated agent, or the Design Approval Holder with EASA's 
design organization approval, as applicable). For a repair method to 
be approved, the repair approval must specifically refer to this AD.

(j) Inspection After Re-installation

    If any rudder has been inspected as specified in Airbus Service 
Bulletin A300-55-6043, Revision 01, dated December 3, 2007; or A310-
55-2044, Revision 01, dated

[[Page 11358]]

December 3, 2007; as applicable; and has been removed and re-
installed on any airplane after this inspection, that rudder must be 
re-inspected as required by paragraph (g) of this AD; and all 
applicable actions required by paragraphs (h) and (i) of this AD 
must be done.

(k) Parts Installation Limitation

    As of the effective date of this AD, no person may install, on 
any airplane, a rudder assembly having a part number starting with 
A55471500, unless it has been inspected as required by paragraph (h) 
of this AD, and all applicable actions required by paragraph (i) of 
this AD have been done.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; telephone (425) 227-2125; 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). You 
are required to ensure the product is airworthy before it is 
returned to service.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0039, dated February 26, 
2013; for related information, which can be found in the AD docket 
on the Internet at http://www.regulations.gov.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@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.

    Issued in Renton, Washington, on February 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04495 Filed 2-27-14; 8:45 am]
BILLING CODE 4910-13-P
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