```

[Federal Register Volume 79, Number 40 (Friday, February 28, 2014)]
[Proposed Rules]
[Pages 11358-11360]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04496]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0124; Directorate Identifier 2012-NM-197-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 all 
Airbus Model A300 series airplanes. This proposed AD was prompted by an 
analysis of the impacts of extended service goal activities on Airbus 
Model A300 series airplanes. This proposed AD would require revising 
the maintenance program. We are proposing this AD to prevent failure of 
flight critical systems.

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.

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-
0124; or in person at the Docket Management Facility 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-2014-0124; 
Directorate Identifier 2012-NM-197-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 2012-0233, dated November 7, 2012 (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:

    The results of the Extended Service Goal (ESG) exercise for A300 
series aeroplanes (75,000 flight hours (FH) or 48,000 flight cycles 
(FC), whichever occurs first) identified certain operational tests 
as Airworthiness Limitation Items (ALI), necessary to ensure the 
safety objectives for aeroplanes which have accumulated or exceeded 
60,000 FH.
    These ALI are not fully new, since all nine tasks derive from 
existing Maintenance Planning Document (MPD) tasks. Consequently, 
the intervals of those nine tasks can no longer be escalated or 
retained at an interval higher than that specified in this [EASA] AD 
for each task.
    Failure to comply with these tasks within the established 
maximum intervals could be detrimental to the safety of the affected 
aeroplanes.

[[Page 11359]]

    For the reasons described above, this [EASA] AD requires the 
implementation of nine specific operational ALI test for aeroplanes 
which have accumulated or exceeded 60,000 FH.
    In addition, Airbus performed an analysis of the impacts of ESG 
activities on A300 series aeroplanes and, based on the results, this 
[EASA] AD publishes an operational life of 75,000 FH or 48,000 FC, 
whichever occurs first, applicable to A300 system installations.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2014-0124.

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

    We estimate that this proposed AD affects 7 airplanes of U.S. 
registry.
    We also estimate that it would take about 1 work-hour 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 $595, or $85 per product.

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-2014-0124; Directorate Identifier 2012-NM-
197-AD.

(a) Comments Due Date

    We must receive comments by April 14, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 airplanes, certificated in any 
category, all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 05 Periodic 
Inspections; Code 22, Auto Flight; Code 27, Flight Controls.

(e) Reason

    This AD was prompted by an analysis of the impacts of extended 
service goal activities on Airbus Model A300 series airplanes. We 
are issuing this AD to prevent failure of flight critical systems.

(f) Compliance

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

(g) Maintenance/Inspection Program Revision

    Within 90 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
information specified in Table 1 to paragraph (g) of this AD. The 
compliance time for doing the initial actions specified in Table 1 
to paragraph (g) of this AD is before 60,000 total flight hours 
accumulated on the airplane, or within 90 days after the effective 
date of this AD, whichever occurs later.

              Table 1 to Paragraph (g) of This AD: Intervals for New Airworthiness Limitation Items
----------------------------------------------------------------------------------------------------------------
                                                                      Interval (not to
  Maintenance Planning Document Task          Task description         exceed) (flight    Aircraft maintenance
                 No.                                                       hours)           manual reference
----------------------------------------------------------------------------------------------------------------
273311 0503 1........................  ARTIFICIAL FEEL-ELEVATOR--                2,500  273300/501.
                                        Operational test of pitch
                                        artificial feel by comparing
                                        qualitatively operating
                                        loads in high-speed and low-
                                        speed configurations (with
                                        each individual hydraulic
                                        system).
273313 0503 1........................  COMPUTER-ARTIFICIAL FEEL--                3,500  272300/501
                                        Operational test of                             and
                                        artificial feel ``pitch                         273300/501.
                                        feel'' and ``rudder travel''
                                        monitoring circuits (warning
                                        light test and indicating
                                        system test).
222100 0503 1........................  YAW DAMPER--Operational test                 80  222100/501.
                                        to verify correct operation
                                        of mechanical control
                                        between yaw damper system 2
                                        and the rudder.

[[Page 11360]]

 
222600 0503 1........................  YAW DAMPER--Operational test                 80  222600/501.
                                        to verify correct operation
                                        of mechanical control
                                        between yaw damper system 2
                                        and the rudder.
272411 0503 1........................  SERVO CONTROL-RUDDER--                      250  271400/501.
                                        Operational test of rudder
                                        servo controls (with
                                        individual hydraulic system)
                                        by moving right-hand (RH)
                                        rudder pedal full forward
                                        and visually observe that
                                        rudder moves to the right.
                                        Check that rudder travel is
                                        confirmed on the flight
                                        control position indicator.
                                        Release RH pedal. Repeat
                                        above test by moving left-
                                        hand rudder pedal..
275400 0503 1........................  FLAP ASYMMETRY--Operational                 500  275400/501.
                                        test of flap asymmetry
                                        monitoring circuit (include
                                        solenoid operation).
275400 0503 2........................  FLAP PRESSURE-OFF BRAKE--                 1,000  275400/501.
                                        Operational test of pressure-
                                        off brake.
278300 0503 1........................  SLAT ASYMMETRY--Operational                 500  278300/501.
                                        test of slat asymmetry
                                        monitoring circuit.
278300 0503 2........................  SLAT PRESSURE-OFF BRAKE--                 1,000  278300/501.
                                        Operational test of pressure-
                                        off brake.
----------------------------------------------------------------------------------------------------------------

(h) Airplane Airworthiness Limitation

    As of the effective date of this AD, do not operate any airplane 
beyond 75,000 total flight hours or 48,000 total flight cycles, 
whichever occurs first.

(i) No Alternative Actions and Intervals

    After accomplishing the revision required by paragraph (g) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used unless the actions or intervals are approved as an 
alternative method of compliance in accordance with the procedures 
specified in paragraph (j)(1) of this AD.

(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, 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: 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 DAH with a State of Design Authority's 
design organization approval). For a repair method to be approved, 
the repair approval must specifically refer to this AD. You are 
required to ensure the product is airworthy before it is returned to 
service.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Aviation Safety Agency Airworthiness Directive 2012-0233, 
dated November 7, 2012, 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 it in Docket No. FAA-2014-0124.

    Issued in Renton, Washington, on February 14, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04496 Filed 2-27-14; 8:45 am]
BILLING CODE 4910-13-P
```