Document ID: FAA-2010-1278-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Posted Date: 2011-01-05T05:00Z

[Federal Register Volume 76, Number 3 (Wednesday, January 5, 2011)]
[Rules and Regulations]
[Pages 441-444]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32995]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1278; Directorate Identifier 2010-NM-260-AD; 
Amendment 39-16567; AD 2011-01-13]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and 
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes 
(Collectively Called A300-600 Series Airplanes)

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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[[Page 442]]

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    During a routine maintenance check on an A300-600 aeroplane, the 
operator found the pitch uncoupling unit installed at an incorrect 
location. The pitch uncoupling unit was inverted with the rod 
assembly.
    After a complete inspection of all A300-600 aeroplanes of its 
fleet, the operator identified the same incorrect installation on 
another aeroplane.
* * * * *
    This condition, if not detected and corrected, in combination 
with particular failure modes, could lead to loss of control of the 
aeroplane during the takeoff phase.

* * * * *
This AD requires actions that are intended to address the unsafe 
condition described in the MCAI.

DATES: This AD becomes effective January 20, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of January 20, 
2011.
    We must receive comments on this AD by February 22, 2011.

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 W12-40, 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; 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 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, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Emergency Airworthiness Directive 2010-0239-E, dated November 19, 2010 
[Corrected November 23, 2010] (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    During a routine maintenance check on an A300-600 aeroplane, the 
operator found the pitch uncoupling unit installed at an incorrect 
location. The pitch uncoupling unit was inverted with the rod 
assembly.
    After a complete inspection of all A300-600 aeroplanes of its 
fleet, the operator identified the same incorrect installation on 
another aeroplane.
Had this routine maintenance check, which was accomplished for other 
purposes, not been carried out, the incorrect installation could 
only have been detected during the accomplishment of the pitch 
uncoupling functional test.

    Note:  Another maintenance task, the pitch uncoupling 
operational test, scheduled at intervals not to exceed 2,000 FH or 
36 months, whichever occurs first (MPD task 273100-01-1), only 
validates the condition of the pitch uncoupling solenoid.

    This condition, if not detected and corrected, in combination 
with particular failure modes, could lead to loss of control of the 
aeroplane during the takeoff phase.
    For the reason described above, this AD requires a one time 
visual inspection, to detect any incorrect installation of the pitch 
uncoupling unit,and, depending on findings, to take corrective 
actions.
    This [EASA] AD was republished to correct the compliance time.

    Corrective actions include removing and re-installing the pitch 
uncoupling unit and rod assembly at the correction location and doing a 
functional test to verify correct operation. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued A300-600 All Operators Telex 27A6068, Revision 
01, dated November 18, 2010. 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 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the AD.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because a 
pitch uncoupling unit was found to be installed at an incorrect 
location. The pitch uncoupling unit was inverted with the rod assembly. 
This condition, if not detected and corrected, in combination with 
other failure modes, could lead to loss of control of the airplane 
during the take-off phase. Therefore, we determined that notice and 
opportunity for public comment before issuing this AD are impracticable 
and that good cause exists for making this amendment effective in fewer 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2010-1278; Directorate 
Identifier 2010-NM-260-

[[Page 443]]

AD'' at the beginning of your comments. We specifically invite comments 
on the overall regulatory, economic, environmental, and energy aspects 
of this AD. We will consider all comments received by the closing date 
and may amend this AD because of 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 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    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); and
    3. 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 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.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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 AD:

2011-01-13 Airbus: Amendment 39-16567. Docket No. FAA-2010-1278; 
Directorate Identifier 2010-NM-260-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
20, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to 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 serial numbers, except 
for airplanes on which the pitch uncoupling functional test has 
already been performed in service since new.

    Note 1: The pitch uncoupling functional test is described in 
Section 3.D.(2) of task 27-31-00, Page Block 501 of Airbus A300-600 
Aircraft Maintenance Manual (AMM) [Maintenance Planning Document 
(MPD) task 273100-02-1].

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
Controls.

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:
    During a routine maintenance check on an A300-600 aeroplane, the 
operator found the pitch uncoupling unit installed at an incorrect 
location. The pitch uncoupling unit was inverted with the rod 
assembly.
    After a complete inspection of all A300-600 aeroplanes of its 
fleet, the operator identified the same incorrect installation on 
another aeroplane.
* * * * *
    This condition, if not detected and corrected, in combination 
with particular failure modes, could lead to loss of control of the 
aeroplane during the takeoff phase.
* * * * *

Compliance

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

Inspection, Re-Installation, and Functional Test

    (g) Within 30 days after the effective date of this AD, do a 
general visual inspection for correct location of the pitch 
uncoupling unit, in accordance with paragraph 4.2 of Airbus A300-600 
All Operators Telex (AOT) 27A6068, Revision 01, dated November 18, 
2010. If the pitch uncoupling unit is found inverted with the rod 
assembly, before further flight, remove and re-install the 
uncoupling unit and the rod assembly at their correct locations and 
do a functional test of the pitch uncoupling unit to verify correct 
operation, in accordance with paragraph 4.2 of Airbus A300-600 AOT 
27A6068, Revision 01, dated November 18, 2010.

FAA AD Differences

    Note 2:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (h) 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. Send information to ATTN: Dan 
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. 
Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards 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.
    (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

[[Page 444]]

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.

Related Information

    (i) Refer to MCAI European Aviation Safety Agency Emergency 
Airworthiness Directive 2010-0239-E, dated November 19, 2010 
[Corrected November 23, 2010]; and Airbus A300-600 AOT 27A6068, 
Revision 01, dated November 18, 2010; for related information.

Material Incorporated by Reference

    (j) You must use Airbus A300-600 All Operators Telex 27A6068, 
Revision 01, dated November 18, 2010, to do the actions required by 
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 22, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-32995 Filed 1-4-11; 8:45 am]
BILLING CODE 4910-13-P