[Federal Register Volume 81, Number 130 (Thursday, July 7, 2016)]
[Proposed Rules]
[Pages 44244-44246]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-15862]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8161; Directorate Identifier 2016-CE-018-AD]
RIN 2120-AA64


Airworthiness Directives; REIMS AVIATION S.A. Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain REIMS AVIATION S.A. Model F406 airplanes. 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 cracks found in the horizontal stabilizer rear 
attach structure and the vertical fin rear spar attach structure. We 
are issuing this proposed AD to require actions to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by August 22, 2016.

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 ASI 
Aviation,

[[Page 44245]]

A[eacute]rodrome de Reims Prunay, 51360 Prunay, France; telephone: +33 
3 26 48 46 84; fax: +33 3 26 49 18 57; email: [email protected]; 
Internet: http://asi-aviation.fr/page-Accueil.html. You may review this 
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 by searching for and locating Docket No. FAA-2016-
8161; 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; email: 
[email protected].

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-2016-8161; 
Directorate Identifier 2016-CE-018-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No.: 2016-0101, dated May 25, 2016 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    Fatigue cracks and holes elongation were found on horizontal 
stabilizer fittings on F406 aeroplanes having accumulated more than 
2 500 flight hours (FH).
    This condition, if not detected and corrected, could result in 
loss of structural integrity of the horizontal stabilizer fittings.
    To initially address this issue, DGAC France published AD 2001-
161 to require repetitive visual inspections of the fittings, and, 
dependings on findings, replacement with a serviceable part.
    Since that AD was issued, during maintenance, cracks were found 
on a slice plate of horizontal stabilizer fittings. Consequently, 
ASI Aviation issued Service Bulletin (SB) CAB01-5 Revision 2 to 
provide instructions for additional eddy-current non-destructive 
test (NDT) inspections.
    For the reasons described above, this AD retains the 
requirements of DGAC France AD 2001-161, which is superseded, and 
requires the additional NDT inspections.

    You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8161.

Related Service Information Under 1 CFR Part 51

    ASI Aviation has issued Service Bulletin CAB01-5 Rev 2, dated 
December 3, 2015. The service information describes procedures for 
inspecting the horizontal stabilizer rear attach structure and the 
vertical fin rear spar attach structure for cracks and oversized bolt 
holes and making all necessary repairs and replacements. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section of this NPRM.

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.

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 20.5 work-hours per 
product to comply with the basic inspections requirements of this 
proposed AD (18 work-hours to remove the horizontal stabilizer to gain 
access for the inspection and 2.5 work-hours to do the inspection). The 
average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the proposed 
inspection on U.S. operators to be $12,197.50, or $1,742.50 per 
product.
    We estimate that it would take about 25 work-hours per product to 
reinstall the horizontal stabilizer after doing the proposed inspection 
and any proposed necessary repairs or replacements. Based on these 
figures, we estimate the cost of this proposed action on U.S. operators 
to be $14,875, or $2,125 per product.
    In addition, we estimate any proposed necessary corrective actions 
as follows:

--Installing Service Kit SKRA406-11--Rev. 2 would take about 3 work-
hours and require parts costing $65, for a cost of $320 per product. We 
have no way of determining the number of products that may need this 
action.
--Installing Service Kit SK406-137 (which superseded Service Kit 
SKRA406-12--Rev. 2) would take about 20 work-hours and require parts 
costing $2,000, for a cost of $3,800 per product. We have no way of 
determining the number of products that may need this action.
--Installing Service Kit SKRA406-13--Rev. 2 would take about 8 work-
hours and require parts costing $1,800, for a cost of $2,480 per 
product. We have no way of determining the number of products that may 
need this action.

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.

[[Page 44246]]

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

REIMS AVIATION S.A.: Docket No. FAA-2016-8161; Directorate 
Identifier 2016-CE-018-AD.

(a) Comments Due Date

    We must receive comments by August 22, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to REIMS AVIATION S.A. F406 airplanes, serial 
numbers F406-0001 through F406-0098, certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 55: Stabilizers.

(e) Reason

    This AD was prompted by 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 cracks found in 
the horizontal stabilizer rear attach structure and the vertical fin 
rear spar attach structure. We are issuing this AD to prevent 
structural failure of the horizontal stabilizer and/or the vertical 
fin rear spar attach structure, which could result in damage to the 
airplane and loss of control.

 (f) Actions and Compliance

    Unless already done, do the following actions:
    (1) At whichever of the compliance times specified in paragraphs 
(f)(1)(i) through (iii) of this AD that occurs the latest after the 
effective date of this AD, and repetitively thereafter every 2,400 
hours time-in-service (TIS), do a visual and non-destructive test 
(NDT) inspection of the horizontal stabilizer splice plate assembly, 
part number (P/N) 6032183-1 or P/N 406-5518-32183-100 (as 
applicable), and the attach structure assembly P/N 6031210-1. Do the 
inspections following the Accomplishment Instructions in ASI 
Aviation Service Bulletin CAB01-5 Rev 2, dated December 3, 2015.
    (i) Before accumulating 2,500 hours TIS; or
    (ii) Within the next 100 hours TIS; or
    (iii) At the next 600-hour inspection.
    (2) If, during any inspection as required by paragraph (f)(1) of 
this AD, any oversized bolt hole or crack is detected on the 
horizontal stabilizer splice plate assembly or attach structure 
assembly, before further flight, repair or replace the affected part 
with a serviceable part following the Accomplishment Instructions in 
ASI Aviation Service Bulletin CAB01-5 Rev 2, dated December 3, 2015. 
After taking the necessary corrective action, continue with the 
repetitive inspection specified in paragraph (f)(1) of this AD.

(g) Other FAA AD Provisions

    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; email: 
[email protected]. 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.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 
2016-0101, dated 25 May 25, 2016, and ASI Aviation Service Kit 
SKRA40611-Rev. 2, dated December 3, 2015, ASI Service Kit SK406-137, 
dated December 3, 2015 (which superseded ASI Aviation Service Kit 
SKRA406-12-Rev. 2, dated December 3, 2015), and ASI Aviation Service 
Kit SKRA406-13-Rev. 2, dated December 3, 2015, for related 
information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2016-8161. For service information related to this AD, contact ASI 
Aviation, A[eacute]rodrome de Reims Prunay, 51360 Prunay, France; 
telephone: +33 3 26 48 46 84; fax: +33 3 26 49 18 57; email: 
[email protected]; Internet: http://asi-aviation.fr/page-Accueil.html. You may review this 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 June 28, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-15862 Filed 7-6-16; 8:45 am]
 BILLING CODE 4910-13-P