
[Federal Register Volume 76, Number 14 (Friday, January 21, 2011)]
[Proposed Rules]
[Pages 3854-3856]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-1221]


 ========================================================================
 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. 76, No. 14 / Friday, January 21, 2011 / 
Proposed Rules  

[[Page 3854]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0058; Directorate Identifier 2010-CE-071-AD]
RIN 2120-AA64


Airworthiness Directives; REIMS AVIATION S.A. Model F406 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed 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:

    In early 2005, several reports had been received regarding 
discovery of cracks in rudder pulley brackets installed on Reims 
F406 aeroplanes. This pulley bracket, Part Number (P/N) 6015511-1, 
is installed on aeroplanes with the optional ``Camera Hole'' 
modification.
    This condition, if not detected and corrected, could result in 
the loss of rudder control on the airplane.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by March 7, 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 W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Reims Aviation Industries, A[eacute]rodrome de Reims Prunay, 51360 
Prunay, France; telephone + 33 3 26 48 46 65; fax + 33 3 26 49 18 57; 
e-mail Jn.sirot@reims-aviation.fr. You may review copies of the 
referenced service information at the FAA, Small Airplane Directorate, 
901 Locust, Kansas City, Missouri 64106. For information on the 
availability of this material at the FAA, call 816-329-4148.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 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: Albert Mercado, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090.

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-2011-0058; 
Directorate Identifier 2010-CE-071-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 because of those comments.
    We will post all comments we receive, without change, to http://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

    On January 12, 2007, we issued AD 2007-02-12, Amendment 39-14899 
(72 FR 3047; January 24, 2007). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2007-02-12, REIMS AVIATION S.A. discovered that 
airplane serial number (SN) F406-0091 had inadvertently not been 
included in the service information and has revised the service 
information to correct the omission.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No.: 2010-0230, dated November 5, 2010 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    In early 2005, several reports had been received regarding 
discovery of cracks in rudder pulley brackets installed on Reims 
F406 aeroplanes. This pulley bracket, Part Number (P/N) 6015511-1, 
is installed on aeroplanes with the optional ``Camera Hole'' 
modification.
    This condition, if not detected and corrected, could result in 
the loss of rudder control on the airplane.
    To address this unsafe condition, DGAC France issued Emergency 
(Urgent) AD UF-2005-080, followed by the final AD F-2005-080, 
requiring repetitive inspections of the P/N 6015511-1 rudder pulley 
bracket and replacement of the bracket with a modified bracket, P/N 
4061-2701-1, as terminating action.
    Recently, Reims discovered that aeroplane s/n F406-0091 had 
inadvertently not been included in the SB and this has been revised 
to correct the omission.
    For the reasons described above, this AD retains the 
requirements of DGAC France AD F-2005-080, which is superseded, and 
adds aeroplane s/n F406-0091 to the Applicability of the AD, by 
referencing Revision 2 of the Reims Aviation Industries SB F406-58.

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

Relevant Service Information

    Reims Aviation S.A. has issued Reims Aviation Industries Service 
Bulletin No. F406-58, REV 1, dated October 27,

[[Page 3855]]

2006; and Reims Aviation Industries Service Bulletin No. F406-58, REV 
2, dated July 27, 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 the 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 this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Differences Between This Proposed 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 proposed 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 proposed AD.

Costs of Compliance

    We estimate that this proposed AD will affect 7 products of U.S. 
registry. We also estimate that it would take about 11 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 $750 per product.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $11,795, or $1,685 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); 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 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 removing Amendment 39-14899 (72 FR 
3047; January 24, 2007), and adding the following new AD:

Reims Aviation S.A.: Docket No. FAA-2011-0058; Directorate 
Identifier 2010-CE-071-AD.

Comments Due Date

    (a) We must receive comments by March 7, 2011.

Affected ADs

    (b) This AD supersedes AD 2007-02-12, Amendment 39-14899.

Applicability

    (c) This AD applies to Reims Aviation S.A. Model F406 airplanes, 
serial numbers (SNs) 0002, 0003, 0004, 0006, 0008, 0009, 0010, 0012, 
0013, 0017, 0024, 0025, 0039, 0042, 0044, 0045, 0066, 0070, 0073, 
0074, 0075, 0077, 0080 through 0092, certificated in any category.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    In early 2005, several reports had been received regarding 
discovery of cracks in rudder pulley brackets installed on Reims 
F406 aeroplanes. This pulley bracket, Part Number (P/N) 6015511-1, 
is installed on aeroplanes with the optional ``Camera Hole'' 
modification.
    This condition, if not detected and corrected, could result in 
the loss of rudder control on the airplane.
    To address this unsafe condition, DGAC France issued Emergency 
(Urgent) AD UF-2005-080, followed by the final AD F-2005-080, 
requiring repetitive inspections of the P/N 6015511-1 rudder pulley 
bracket and replacement of the bracket with a modified bracket, P/N 
4061-2701-1, as terminating action.
    Recently, Reims discovered that aeroplane s/n F406-0091 had 
inadvertently not been included in the SB and this has been revised 
to correct the omission.
    For the reasons described above, this AD retains the 
requirements of DGAC France AD F-2005-080, which is superseded, and 
adds aeroplane s/n F406-0091 to the Applicability of the AD, by 
referencing Revision 2 of the Reims Aviation Industries SB F406-58.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) For all affected SNs except F406-0091:
    (i) Within the next 10 hours time-in-service (TIS) after 
February 13, 2007 (the effective date retained from AD 2007-02-12), 
perform the initial inspection as specified in Reims Aviation 
Industries Service Bulletin No. F406-58, REV 1, dated October 27, 
2006; or Reims Aviation Industries Service Bulletin No. F406-58, REV 
2, dated July 27, 2010.
    (ii) If no cracking is found following the initial inspection 
required in paragraph (f)(1)(i) of this AD, repetitively thereafter 
inspect every 50 hours TIS or 1 month, whichever occurs first, until 
the installation of the modified pulley bracket specified in 
paragraphs (f)(1)(iii) or (f)(1)(iv) of this AD is done.
    (iii) If any cracking is found during the inspection required in 
paragraph (f)(1)(i) of this AD, before further flight, install the

[[Page 3856]]

modified pulley bracket as specified in Reims Aviation Industries 
Service Bulletin No. F406-58, REV 1, dated October 27, 2006; or 
Reims Aviation Industries Service Bulletin No. F406-58, REV 2, dated 
July 27, 2010. This installation terminates the repetitive 
inspections required in paragraph (f)(1)(ii) of this AD.
    (iv) Within the next 100 hours TIS or 2 months after February 
13, 2007 (the effective date retained from AD 2007-02-12), whichever 
occurs first, install the modified pulley bracket as specified in 
Reims Aviation Industries Service Bulletin No. F406-58, REV 1, dated 
October 27, 2006; or Reims Aviation Industries Service Bulletin No. 
F406-58, REV 2, dated July 27, 2010. This installation terminates 
the repetitive inspections required in paragraph (f)(1)(ii) of this 
AD.
    (v) The modified pulley bracket specified in Reims Aviation 
Industries Service Bulletin No. F406-58, REV 1, dated October 27, 
2006; or Reims Aviation Industries Service Bulletin No. F406-58, REV 
2, dated July 27, 2010, may be installed at any time after the 
inspection required in paragraph (f)(1)(i) of this AD, as long as no 
cracking is found, but no later than the compliance time specified 
in paragraph (f)(1)(iv) of this AD. If cracking is found, it must be 
replaced before further flight as required in paragraph (f)(1)(iii) 
of this AD.
    (2) For serial number F406-0091:
    (i) Within the next 10 hours TIS after the effective of this AD, 
perform the initial inspection as specified in Reims Aviation 
Industries Service Bulletin No. F406-58, REV 2, dated July 27, 2010.
    (ii) If no cracking is found following the initial inspection 
required in paragraph (f)(2)(i) of this AD, repetitively thereafter 
inspect every 50 hours TIS or 1 month, whichever occurs first, until 
the installation of the modified pulley bracket specified in 
paragraphs (f)(2)(iii) and (f)(2)(iv) of this AD is done.
    (iii) If any cracking is found during the inspection required in 
paragraph (f)(2)(i) of this AD, before further flight, install the 
modified pulley bracket as specified in Reims Aviation Industries 
Service Bulletin No. F406-58, REV 2, dated July 27, 2010. This 
installation terminates the repetitive inspections required in 
paragraph (f)(2)(ii) of this AD.
    (iv) Within the next 100 hours TIS or 2 months after the 
effective of this AD, whichever occurs first, install the modified 
pulley bracket as specified in Reims Aviation Industries Service 
Bulletin No. F406-58, REV 2, dated July 27, 2010. This installation 
terminates the repetitive inspections required in paragraph 
(f)(2)(ii) of this AD.
    (v) The modified pulley bracket specified in Reims Aviation 
Industries Service Bulletin No. F406-58, REV 2, dated July 27, 2010, 
may be installed at any time after the inspection required in 
paragraph (f)(2)(i) of this AD as long as no cracking is found, but 
no later than the compliance time specified in paragraph (f)(2)(iv) 
of this AD. If cracking is found, it must be replaced before further 
flight as required in paragraph (f)(2)(iii) of this AD.

FAA AD Differences

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

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, 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: Albert Mercado, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4119; fax: (816) 329-4090. Before using 
any approved AMOC on any airplane to which the AMOC applies, notify 
your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO.
    (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: For any reporting requirement in 
this AD, 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.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA) AD 
2010-0230, dated November 5, 2010; Reims Aviation Industries Service 
Bulletin No. F406-58, REV 1, dated October 27, 2006; and Reims 
Aviation Industries Service Bulletin No. F406-58, REV 2, dated July 
27, 2010, for related information. For service information related 
to this AD, contact Reims Aviation Industries, A[eacute]rodrome de 
Reims Prunay, 51360 Prunay, France; telephone + 33 3 26 48 46 65; 
fax + 33 3 26 49 18 57; e-mail Jn.sirot@reims-aviation.fr. You may 
review copies of the referenced service information at the FAA, 
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. 
For information on the availability of this material at the FAA, 
call 816-329-4148.

    Issued in Kansas City, Missouri, on January 14, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-1221 Filed 1-20-11; 8:45 am]
BILLING CODE 4910-13-P


