
[Federal Register Volume 77, Number 36 (Thursday, February 23, 2012)]
[Proposed Rules]
[Pages 10691-10693]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-4208]


 ========================================================================
 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. 77, No. 36 / Thursday, February 23, 2012 / 
Proposed Rules  

[[Page 10691]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0152; Directorate Identifier 2011-NM-059-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 series airplanes; Airbus Model A330-200 Freighter 
series airplanes; Airbus Model A330-300 series airplanes; Airbus Model 
A340-200 series airplanes; and Airbus Model A340-300 series airplanes. 
This proposed AD was prompted by reports of sheared fasteners located 
on the outside skin of the forward cargo door and cracks on the frame 
fork ends, as well as cracks of the aft cargo door frame 64A. This 
proposed AD would require performing a detailed inspection of the outer 
skin rivets at the frame fork ends of the forward and aft cargo door 
for sheared, loose, and missing rivets, repairing the outer skin 
rivets, if necessary, and performing repetitive inspections. We are 
proposing this AD to detect and correct sheared, loose or missing 
fasteners on the forward and aft cargo door frame, which could result 
in the loss of structural integrity of the forward and aft cargo door.

DATES: We must receive comments on this proposed AD by April 9, 2012.

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--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 review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. 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; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 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-2012-0152; 
Directorate Identifier 2011-NM-059-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 2011-0007R1, dated February 14, 2011 (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Two operators have reported cases of some sheared fasteners on 
the outside skin of the forward cargo door, detected during walk 
around checks. Further inspections revealed crack findings on the 
frame (FR) fork ends.
    In addition, during a scheduled maintenance check, the aft cargo 
door frame 64A of an aeroplane has been found cracked for a length 
of more than 3 inches. Outer skin rivets were also found sheared. At 
time of findings the aeroplane had accumulated 10564 flight cycles 
(FC), i.e. below the 12000 FC threshold defined in DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France AD F-2001-124(B) 
and DGAC France AD F-2001-126(B) [which corresponds with FAA AD 
2001-16-01, Amendment 39-12369 (66 FR 40874, August 6, 2001], which 
require a special detailed inspection of the aft cargo compartment 
door.
    In case of cracked or ruptured (forward or aft) cargo door 
frame, the loads will be transferred to the remaining structural 
elements. Such second load path is able to sustain the loads for a 
limited number of flight cycles only. Rupture of two vertical frames 
could result in the loss of the structural integrity of the forward 
or aft cargo door.
    For the above described reasons, this AD requires repetitive 
detailed visual inspections of the aft and forward cargo doors outer 
skin for sheared, loose or missing rivets at all frame fork ends and 
the accomplishment of the applicable corrective actions [repair if 
necessary].
    This [EASA] AD is considered to be an interim action, further 
actions might be required to revise/supersede the above mentioned 
DGAC France ADs.
    This [EASA] AD is revised in order to recognize that aeroplanes 
on which Airbus modification 44852 has been embodied in production 
are not affected by the repetitive inspection requirements of this 
AD on the Aft Cargo Compartment Door.


[[Page 10692]]


You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued the following service information:
     All Operators Telex A330-52A3084, dated December 20, 2010 
(for Model A330-200 and A330-300 series airplanes);
     All Operators Telex A330-52A3085, dated December 20, 2010 
(for Model A330-200 and A330-300 series airplanes);
     All Operators Telex A340-52A4091, dated December 20, 2010 
(for Model A340-200 and A340-300 series airplanes); and
     All Operators Telex A340-52A4092, dated December 20, 2010 
(for Model A340-200 and A340-300 series airplanes).
    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.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 55 products of U.S. registry. We also estimate that 
it would take about 1 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $4,675, or $85 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.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

    Airbus: Docket No. FAA-2012-0152; Directorate Identifier 2011-
NM-059-AD.

(a) Comments Due Date

    We must receive comments by April 9, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and 
-313 airplanes; certificated in any category; all manufacturer 
serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 52: Doors.

(e) Reason

    This AD was prompted by reports of sheared fasteners located on 
the outside skin of the forward cargo door and cracks on the frame 
fork ends, as well as cracks of the aft cargo door frame 64A. We are 
issuing this AD to detect and correct sheared, loose or missing 
fasteners on the forward and aft cargo door frame, which could 
result in the loss of structural integrity of the forward and aft 
cargo door.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Forward Cargo Compartment Door

    Before the accumulation of 6,000 total flight cycles since first 
flight of the airplane or within 400 flight cycles after the 
effective date of this AD, whichever occurs later: Perform a 
detailed inspection of the outer skin rivets at the frame fork ends 
between FR20B and FR25 of the forward cargo door for sheared, loose, 
and missing rivets, in accordance with the instructions of Airbus 
All Operators Telex (AOT) A330-52A3085, dated December 20, 2010 (for 
Model A330-200 and A330-300 series airplanes); or Airbus AOT A340-
52A4092, dated December 20, 2010 (for Model A340-200 and A340-300 
series airplanes). Thereafter repeat the inspection at intervals not 
to exceed 800 total flight cycles.

(h) Aft Cargo Compartment Door

    For all airplanes, except those on which Airbus Modification 
44854 or Modification 44852 has been embodied in production, or 
Airbus Service Bulletin A330-52-3044 or Airbus Service Bulletin 
A340-52-4054 has been embodied in service: Before the accumulation 
of 4,000 total flight cycles since first flight of the airplane, or 
within 400 flight cycles after the effective date of this AD, 
whichever occurs later, perform a detailed inspection of outer skin 
rivets at the frame fork ends between FR60 and FR64A of the aft 
cargo door for sheared, loose or missing rivets, in accordance with 
the instructions of Airbus AOT A330-52A3084, dated December 20, 2010 
(for Model A330-

[[Page 10693]]

200 and A330-300 series airplanes); or Airbus AOT A340-52A4091, 
dated December 20, 2010 (for Model A340-200 and A340-300 series 
airplanes). Thereafter repeat the inspection at intervals not to 
exceed 400 flight cycles.

(i) Corrective Action

    If any sheared, loose, or missing rivets are found during any 
inspection required by paragraph (g) or (h) of this AD: Before 
further flight, repair using a method approved by the Manager, 
International Branch, ANM-116, FAA; or European Aviation Safety 
Agency (EASA) (or its delegated agent).

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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, Washington 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(k) Related Information

    Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2011-0007R1, dated February 14, 2011, and the service 
information specified in paragraphs (k)(1) through (k)(4) of this 
AD, for related information.
    (1) Airbus All Operators Telex (AOT) A330-52A3085, dated 
December 20, 2010.
    (2) Airbus AOT A340-52A4092, dated December 20, 2010.
    (3) Airbus AOT A330-52A3084, dated December 20, 2010.
    (4) Airbus AOT A340-52A4091, dated December 20, 2010.

    Issued in Renton, Washington, on February 14, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-4208 Filed 2-22-12; 8:45 am]
BILLING CODE 4910-13-P


