81 FR 44244 - Airworthiness Directives; REIMS AVIATION S.A. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 130 (July 7, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 130 (July 7, 2016)
| Page Range | 44244-44246 | |
| FR Document | 2016-15862 |
[Federal Register Volume 81, Number 130 (Thursday, July 7, 2016)] [Proposed Rules] [Pages 44244-44246] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-15862] ----------------------------------------------------------------------- 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). ----------------------------------------------------------------------- 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
![44244 Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
(d) Subject using the procedures found in 14 CFR 39.19. information on the availability of this
Air Transport Association (ATA) of In accordance with 14 CFR 39.19, send your material at the FAA, call 425–227–1221.
America Code 53, Fuselage. request to your principal inspector or local
Issued in Renton, Washington, on June 23,
Flight Standards District Office, as
(e) Reason 2016.
appropriate. If sending information directly
to the International Branch, send it to ATTN: Dorr M. Anderson,
This AD was prompted by reports of cracks
in the frame base fittings connecting the Dan Rodina, Aerospace Engineer, Acting Manager, Transport Airplane
frame lower positions to the center wing box. International Branch, ANM–116, Transport Directorate, Aircraft Certification Service.
We are issuing this AD to detect and correct Airplane Directorate, FAA, 1601 Lind [FR Doc. 2016–15928 Filed 7–6–16; 8:45 am]
cracking of the lower frame fittings, which Avenue SW., Renton, WA 98057–3356;
BILLING CODE 4910–13–P
could result in reduced structural integrity of telephone 425–227–1405; fax 425–227–2125.
the airplane. Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using
(f) Compliance any approved AMOC, notify your appropriate DEPARTMENT OF TRANSPORTATION
Comply with this AD within the principal inspector, or lacking a principal
compliance times specified, unless already inspector, the manager of the local flight Federal Aviation Administration
done. standards district office/certificate holding
district office. The AMOC approval letter 14 CFR Part 39
(g) Repetitive Inspections and Replacement
must specifically reference this AD. [Docket No. FAA–2016–8161; Directorate
If Necessary
(2) Contacting the Manufacturer: For any Identifier 2016–CE–018–AD]
At the applicable time specified in requirement in this AD to obtain corrective
paragraph 1.E., ‘‘Compliance,’’ of Airbus actions from a manufacturer, the action must RIN 2120–AA64
Service Bulletin A300–53–6177, dated May be accomplished using a method approved
20, 2015, except where Airbus Service by the Manager, International Branch, ANM– Airworthiness Directives; REIMS
Bulletin A300–53–6177, dated May 20, 2015, 116, Transport Airplane Directorate, FAA; or AVIATION S.A. Airplanes
specifies a compliance time ‘‘from issuance the European Aviation Safety Agency
of Revision 04 of Service Bulletin A300–53– (EASA); or Airbus’s EASA Design AGENCY: Federal Aviation
6111,’’ this AD requires compliance within Organization Approval (DOA). If approved by Administration (FAA), Department of
the specified compliance time after the the DOA, the approval must include the Transportation (DOT).
effective date of this AD: Perform a detailed DOA-authorized signature.
inspection for cracking of the lower frame ACTION: Notice of proposed rulemaking
(3) Reporting Requirements: A federal
fittings between frame (FR) 41 and FR46 of (NPRM).
agency may not conduct or sponsor, and a
the frame foot, and if any crack is found, person is not required to respond to, nor
before further flight, replace with a new SUMMARY: We propose to adopt a new
shall a person be subject to a penalty for
frame foot, in accordance with the airworthiness directive (AD) for certain
failure to comply with a collection of
Accomplishment Instructions of Airbus information subject to the requirements of REIMS AVIATION S.A. Model F406
Service Bulletin A300–53–6177, dated May the Paperwork Reduction Act unless that airplanes. This proposed AD results
20, 2015. Repeat the inspection thereafter at collection of information displays a current from mandatory continuing
the applicable intervals specified in valid OMB Control Number. The OMB airworthiness information (MCAI)
paragraph 1.E., ‘‘Compliance,’’ of Airbus Control Number for this information originated by an aviation authority of
Service Bulletin A300–53–6177, dated May collection is 2120–0056. Public reporting for
20, 2015.
another country to identify and correct
this collection of information is estimated to an unsafe condition on an aviation
(h) Reporting be approximately 5 minutes per response, product. The MCAI describes the unsafe
including the time for reviewing instructions,
At the applicable time specified in condition as cracks found in the
completing and reviewing the collection of
paragraph (h)(1) or (h)(2) of this AD: Submit horizontal stabilizer rear attach
a report of the findings (both positive and information. All responses to this collection
of information are mandatory. Comments structure and the vertical fin rear spar
negative) of each inspection required by attach structure. We are issuing this
paragraph (g) of this AD. Send the report to concerning the accuracy of this burden and
Airbus Service Bulletin Reporting Online suggestions for reducing the burden should proposed AD to require actions to
Application on Airbus World (https:// be directed to the FAA at: 800 Independence address the unsafe condition on these
w3.airbus.com). Ave. SW., Washington, DC 20591, Attn: products.
(1) If the inspection was done on or after Information Collection Clearance Officer,
AES–200. DATES: We must receive comments on
the effective date of this AD: Submit the this proposed AD by August 22, 2016.
report within 30 days after the inspection. (k) Related Information
(2) If the inspection was done before the ADDRESSES: You may send comments by
effective date of this AD: Submit the report (1) Refer to Mandatory Continuing any of the following methods:
within 30 days after the effective date of this Airworthiness Information (MCAI) EASA • Federal eRulemaking Portal: Go to
AD. Airworthiness Directive 2015–0217, dated http://www.regulations.gov. Follow the
October 30, 2015, for related information.
(i) Optional Terminating Action This MCAI may be found in the AD docket
instructions for submitting comments.
on the Internet at http://www.regulations.gov • Fax: (202) 493–2251.
Replacement of all lower frame feet • Mail: U.S. Department of
between FR41 and FR46, in accordance with by searching for and locating Docket No.
the Accomplishment Instructions of Airbus FAA–2014–0143. Transportation, Docket Operations, M–
Service Bulletin A300–53–6176, dated May (2) For service information identified in 30, West Building Ground Floor, Room
20, 2015, terminates the repetitive this AD, contact Airbus SAS, Airworthiness W12–140, 1200 New Jersey Avenue SE.,
inspections required by paragraph (g) of this Office—EAW, 1 Rond Point Maurice Washington, DC 20590.
AD. Bellonte, 31707 Blagnac Cedex, France; • Hand Delivery: U.S. Department of
telephone +33 5 61 93 36 96; fax +33 5 61 Transportation, Docket Operations, M–
Lhorne on DSK30JT082PROD with PROPOSALS
(j) Other FAA AD Provisions 93 44 51; email account.airworth-eas@ 30, West Building Ground Floor, Room
The following provisions also apply to this airbus.com; Internet http://www.airbus.com.
You may view this referenced service
W12–140, 1200 New Jersey Avenue SE,
AD:
(1) Alternative Methods of Compliance information at the FAA, Transport Airplane Washington, DC 20590, between 9 a.m.
(AMOCs): The Manager, International Directorate, 1601 Lind Avenue SW., Renton, and 5 p.m., Monday through Friday,
Branch, ANM–116, Transport Airplane WA. You may view this service information except Federal holidays.
Directorate, FAA, has the authority to at the FAA, Transport Airplane Directorate, For service information identified in
approve AMOCs for this AD, if requested 1601 Lind Avenue SW., Renton, WA. For this proposed AD, contact ASI Aviation,
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![44246 Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules
Regulatory Findings originated by an aviation authority of another person is not required to respond to, nor
country to identify and correct an unsafe shall a person be subject to a penalty for
We determined that this proposed AD condition on an aviation product. The MCAI failure to comply with a collection of
would not have federalism implications describes the unsafe condition as cracks information subject to the requirements of
under Executive Order 13132. This found in the horizontal stabilizer rear attach the Paperwork Reduction Act unless that
proposed AD would not have a structure and the vertical fin rear spar attach collection of information displays a current
substantial direct effect on the States, on structure. We are issuing this AD to prevent valid OMB Control Number. The OMB
the relationship between the national structural failure of the horizontal stabilizer Control Number for this information
Government and the States, or on the and/or the vertical fin rear spar attach collection is 2120–0056. Public reporting for
structure, which could result in damage to this collection of information is estimated to
distribution of power and be approximately 5 minutes per response,
the airplane and loss of control.
responsibilities among the various including the time for reviewing instructions,
levels of government. (f) Actions and Compliance completing and reviewing the collection of
For the reasons discussed above, I Unless already done, do the following information. All responses to this collection
certify this proposed regulation: actions: of information are mandatory. Comments
(1) Is not a ‘‘significant regulatory (1) At whichever of the compliance times concerning the accuracy of this burden and
action’’ under Executive Order 12866, specified in paragraphs (f)(1)(i) through (iii) suggestions for reducing the burden should
(2) Is not a ‘‘significant rule’’ under of this AD that occurs the latest after the be directed to the FAA at: 800 Independence
the DOT Regulatory Policies and effective date of this AD, and repetitively Ave. SW., Washington, DC 20591, Attn:
thereafter every 2,400 hours time-in-service Information Collection Clearance Officer,
Procedures (44 FR 11034, February 26, AES–200.
1979), (TIS), do a visual and non-destructive test
(3) Will not affect intrastate aviation (NDT) inspection of the horizontal stabilizer (h) Related Information
splice plate assembly, part number (P/N)
in Alaska, and Refer to MCAI European Aviation Safety
6032183–1 or P/N 406–5518–32183–100 (as
(4) Will not have a significant Agency (EASA) AD No.: 2016–0101, dated 25
applicable), and the attach structure
economic impact, positive or negative, assembly P/N 6031210–1. Do the inspections
May 25, 2016, and ASI Aviation Service Kit
on a substantial number of small entities SKRA40611–Rev. 2, dated December 3, 2015,
following the Accomplishment Instructions
under the criteria of the Regulatory ASI Service Kit SK406–137, dated December
in ASI Aviation Service Bulletin CAB01–5
3, 2015 (which superseded ASI Aviation
Flexibility Act. Rev 2, dated December 3, 2015.
Service Kit SKRA406–12–Rev. 2, dated
(i) Before accumulating 2,500 hours TIS; or December 3, 2015), and ASI Aviation Service
List of Subjects in 14 CFR Part 39 (ii) Within the next 100 hours TIS; or Kit SKRA406–13–Rev. 2, dated December 3,
Air transportation, Aircraft, Aviation (iii) At the next 600-hour inspection. 2015, for related information. You may
safety, Incorporation by reference, (2) If, during any inspection as required by examine the MCAI on the Internet at http://
Safety. paragraph (f)(1) of this AD, any oversized bolt www.regulations.gov by searching for and
hole or crack is detected on the horizontal locating Docket No. FAA–2016–8161. For
The Proposed Amendment stabilizer splice plate assembly or attach service information related to this AD,
Accordingly, under the authority structure assembly, before further flight, contact ASI Aviation, Aérodrome de Reims
repair or replace the affected part with a Prunay, 51360 Prunay, France; telephone:
delegated to me by the Administrator,
serviceable part following the +33 3 26 48 46 84; fax: +33 3 26 49 18 57;
the FAA proposes to amend 14 CFR part Accomplishment Instructions in ASI
39 as follows: email: contact@ask-aviation.fr; Internet:
Aviation Service Bulletin CAB01–5 Rev 2, http://asi-aviation.fr/page-Accueil.html. You
dated December 3, 2015. After taking the may review this referenced service
PART 39—AIRWORTHINESS necessary corrective action, continue with information at the FAA, Small Airplane
DIRECTIVES the repetitive inspection specified in Directorate, 901 Locust, Kansas City,
paragraph (f)(1) of this AD. Missouri 64106. For information on the
■ 1. The authority citation for part 39
(g) Other FAA AD Provisions availability of this material at the FAA, call
continues to read as follows: (816) 329–4148.
Authority: 49 U.S.C. 106(g), 40113, 44701. The following provisions also apply to this
AD: Issued in Kansas City, Missouri, on June
§ 39.13 [Amended] (1) Alternative Methods of Compliance 28, 2016.
■ 2. The FAA amends § 39.13 by adding (AMOCs): The Manager, Standards Office, Pat Mullen,
FAA, has the authority to approve AMOCs Acting Manager, Small Airplane Directorate,
the following new AD:
for this AD, if requested using the procedures Aircraft Certification Service.
REIMS AVIATION S.A.: Docket No. FAA– found in 14 CFR 39.19. Send information to [FR Doc. 2016–15862 Filed 7–6–16; 8:45 am]
2016–8161; Directorate Identifier 2016– ATTN: Albert Mercado, Aerospace Engineer,
CE–018–AD. FAA, Small Airplane Directorate, 901 Locust, BILLING CODE 4910–13–P
(a) Comments Due Date Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4119; fax: (816) 329–
We must receive comments by August 22, 4090; email: albert.mercado@faa.gov. Before DEPARTMENT OF TRANSPORTATION
2016. using any approved AMOC on any airplane
(b) Affected ADs to which the AMOC applies, notify your Federal Aviation Administration
appropriate principal inspector (PI) in the
None.
FAA Flight Standards District Office (FSDO), 14 CFR Part 39
(c) Applicability or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement [Docket No. FAA–2016–7423; Directorate
This AD applies to REIMS AVIATION S.A. Identifier 2016–NM–034–AD]
F406 airplanes, serial numbers F406–0001 in this AD to obtain corrective actions from
through F406–0098, certificated in any a manufacturer or other source, use these RIN 2120–AA64
actions if they are FAA-approved. Corrective
Lhorne on DSK30JT082PROD with PROPOSALS
category.
actions are considered FAA-approved if they Airworthiness Directives; The Boeing
(d) Subject are approved by the State of Design Authority Company Airplanes
Air Transport Association of America (or their delegated agent). You are required
(ATA) Code 55: Stabilizers. to assure the product is airworthy before it AGENCY: Federal Aviation
is returned to service. Administration (FAA), DOT.
(e) Reason (3) Reporting Requirements: For any ACTION: Notice of proposed rulemaking
This AD was prompted by mandatory reporting requirement in this AD, a federal (NPRM).
continuing airworthiness information (MCAI) agency may not conduct or sponsor, and a
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Document Created: 2018-02-08 07:54:28
Document Modified: 2018-02-08 07:54:28
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 22, 2016. | |
| 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] | |
| FR Citation | 81 FR 44244 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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