82 FR 712 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 2 (January 4, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 2 (January 4, 2017)
| Page Range | 712-716 | |
| FR Document | 2016-30117 |
[Federal Register Volume 82, Number 2 (Wednesday, January 4, 2017)] [Rules and Regulations] [Pages 712-716] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-30117] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0143; Directorate Identifier 2012-NM-113-AD; Amendment 39-18753; AD 2016-25-27] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F airplanes. This AD was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. This AD requires repetitive detailed inspections for cracking of the lower frame fittings of the frame foot, and replacement with a new frame foot if cracking is found. This AD also provides optional terminating action for the repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 8, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 8, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0143. 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- 0143; or in person at the Docket Management Facility between 9 a.m. [[Page 713]] 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 Office (telephone: 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. 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: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A300 B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F airplanes. The SNPRM published in the Federal Register on July 7, 2016 (81 FR 44241) (``the SNPRM''). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on March 19, 2014 (79 FR 15266) (``the NPRM''). The NPRM was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. The NPRM proposed to require repetitive detailed inspections of the lower frame fittings, related investigative actions, and corrective actions if necessary. The SNPRM proposed to replace the proposed requirements in the NPRM with new repetitive detailed inspections for cracking of the lower frame fittings of the frame foot, and replacement with a new frame foot if cracking is found. The SNPRM also proposed to provide optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct cracking of the lower frame fittings, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015-0217, dated October 30, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all Airbus Model A300 B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R variant F airplanes. The MCAI states: During accomplishment of Airbus Service Bulletin (SB) A300-53- 6111 (EASA AD 2012-0103), addressing detailed visual inspections of the lower frame fittings between Frame (FR) 41 and FR46, a crack was detected on one A300-600 aeroplane in the area 2 of the foot of FR46 at junction radius level. This frame, previously repaired due to a crack finding in the frame foot area 1, was not due to be inspected before reaching the post-repair inspection threshold, i.e. 45,400 flight cycles since repair embodiment. Further investigation determined that the repairs specified in Airbus SB A300-53-6111 were of limited effect to prevent cracking in the frame foot area 2. This condition, if not detected and corrected, could affect the structural integrity of the fuselage of all aeroplanes operated up to the extended service goal (ESG). As a temporary action and until an improvement of the existing repairs was made available, EASA issued AD 2012-0229 [AD * * *] to require a one-time detailed inspection (DET) of the frame feet that were repaired in accordance with Airbus SB A300-53-6111, and the reporting of findings to Airbus. Since that [EASA] AD was issued, a detailed study was performed resulting in the development of a new inspection programme. Consequently, Airbus cancelled SB A300-53-6111 and replaced it with SB A300-53-6177, introducing repetitive DET of the lower frame fittings between FR41 and FR46 for the entire fleet. In addition to this new inspection programme, Airbus designed a new frame foot which can be installed on aeroplanes through Airbus SB A300-53-6176. For the reasons described above, this [EASA] AD supersedes EASA AD 2012-0103, not retaining its requirements, and instead requires the new inspection programme for the lower frame fittings. This [EASA] AD also introduces an optional terminating action for the repetitive inspections required by the [EASA] AD. Corrective actions include replacing any cracked lower frame fittings with a new frame foot. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0143. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the SNPRM and the FAA's response to each comment. Request To Extend Compliance Time for Reporting Requirement United Parcel Service (UPS) asked that the compliance time for submitting the inspection report specified in paragraph (h) of the proposed AD (in the SNPRM) be extended from 30 to 60 days. UPS stated that accomplishing the inspection may occur many days before the final task signoff (i.e., restoring access due to other work in the area), risking noncompliance with the 30-day requirement. We agree to extend the compliance time for the reporting requirement in this AD to 60 days, because we have determined that this longer compliance time does not affect continued operational safety. We have changed paragraph (i) of this AD accordingly. Request for Clarification of Compliance Time Airbus asked that we clarify the compliance time for the inspections specified in paragraph (g) of the proposed AD (in the SNPRM). Airbus stated that unless Airbus Service Bulletin A300-53-6177, dated May 20, 2015, specifies differently, the inspection thresholds should be counted from the first flight of the airplane, not from the effective date of the AD. Airbus added that the compliance time provided in the proposed AD could be confusing to operators. Airbus also stated that for airplanes on which the inspections have not been done as of the effective date of the AD, no grace period is provided, which is a burden on operators. We agree that clarification is necessary. We agree that the compliance time identified in the ``Threshold'' column of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 20, 2015, refers to accumulated flight cycles or flight hours on the airplane since its first flight, but only if Airbus Service Bulletin A300-53-6177, dated May 20, 2015, does not specify differently. We redesignated paragraph (h) in the SNPRM as paragraph (i) of this AD, and redesignated subsequent paragraphs accordingly. We added clarification of the compliance times for the thresholds in paragraph (h)(1) of this AD. We acknowledge that a grace period was not provided for all configurations. We removed the grace period exception language from paragraph (g) of the proposed AD (in the SNPRM) and moved it to paragraph (h)(2) of this AD. Paragraph (h)(2) of this AD explains that where grace periods specified in Airbus Service Bulletin A300-53-6177, dated May 20, 2015, refer to the issue date of certain service information, those compliance times are after the effective date of the AD. The exception in paragraph (h)(2) of this AD does not apply to compliance times specified as [[Page 714]] thresholds in Airbus Service Bulletin A300-53-6177, dated May 20, 2015. In addition, we have determined that the actions for Configuration 004 airplanes identified in Airbus Service Bulletin A300-53-6177, dated May 20, 2015, must be clarified. For Configuration 004 airplanes identified in Airbus Service Bulletin A300-53-6177, dated May 20, 2015, the actions required by paragraph (g) of this AD cannot be accomplished in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6177, dated May 20, 2015. Paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 20, 2015, specifies the action for Configuration 004 airplanes as contacting and reporting to Airbus. Therefore, we have added paragraph (h)(3) to this AD to require operators to contact the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA), for corrective actions for Configuration 004 airplanes. Request for Clarification of Inspections for Airplanes With a Previously Replaced Frame Foot UPS asked for clarification of the inspection requirements specified in paragraph (g) of the proposed AD (in the SNPRM) for airplanes that previously replaced a frame foot per Airbus Service Bulletin A300-53-6111. UPS stated that if cracking was found during the inspections using that service information there were two options available: Installing a reinforcing doubler on the damaged fitting or replacing the fitting with a new part. UPS added that in Airbus Service Bulletin A300-53-6177, dated May 20, 2015, the inspection requirements are defined for airplanes previously inspected and found with no cracks, or fittings repaired per Airbus Service Bulletin A300-53-6111. UPS noted that it is not clear how to address airplanes on which the cracked fittings were replaced instead of installing a reinforcing repair. UPS asked that fittings replaced with a new part per Airbus Service Bulletin A300-53-6111 be treated as a previously inspected fitting with no crack findings, with repetitive inspections done per Airbus Service Bulletin A300-53-6177, dated May 20, 2015, using Configuration 001 instructions. UPS stated that this proposal is conservative and exceeds the inspection requirements in the proposed AD (in the SNPRM). We agree that clarification is necessary. Airbus Service Bulletin A300-53-6177, dated May 20, 2015, defines four configurations: Configuration 001 for a frame foot that was never repaired, Configuration 002 for a frame foot that was preventatively repaired, Configuration 003 for a frame foot repaired in Area 1 as specified in Airbus Service Bulletin A300-53-6111 or with certain other repairs, and Configuration 004 for any frame foot not addressed by Configurations 1 through 3. If a new frame foot is installed on an airplane, it would be classified as Configuration 001. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-53-6177, dated May 20, 2015. The service information describes procedures for repetitive detailed inspections for cracking of the lower frame fittings between FR41 and FR46. Airbus has also issued Service Bulletin A300-53-6176, dated May 20, 2015. The service information describes procedures for replacing all lower frame feet between frame FR41 and FR46 with new, improved frame feet. 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. Costs of Compliance We estimate that this AD affects 123 airplanes of U.S. registry. We estimate that it takes about 541 work-hours per product to comply with the basic requirements of this AD, and 1 work-hour per product for reporting. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $5,666,610, or $46,070 per product. We estimate that the optional terminating modification will take about 529 work-hours and require parts costing $131,500, for a cost of $176,465. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to 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 control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is 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. 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 that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; [[Page 715]] 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. Adoption of the Amendment 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 airworthiness directive (AD): 2016-25-27 Airbus: Amendment 39-18753; Docket No. FAA-2014-0143; Directorate Identifier 2012-NM-113-AD. (a) Effective Date This AD is effective February 8, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 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. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. We are issuing this AD to detect and correct cracking of the lower frame fittings, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Replacement At the applicable time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 20, 2015, except as required by paragraphs (h)(1) and (h)(2) of this AD: Perform a detailed inspection for cracking of the lower frame fittings between frame (FR) 41 and FR46 of the frame foot, and if any crack is found, before further flight, replace with a new frame foot, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6177, dated May 20, 2015, except as required by paragraph (h)(3) of this AD. Repeat the inspection thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300-53-6177, dated May 20, 2015. (h) Service Information Exceptions (1) Where the threshold identified in the ``Threshold'' column of paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A300- 53-6177, dated May 20, 2015, specifies flight cycles or flight hours without specifying from a repair, replacement, or last inspection, the specified compliance time is accumulated flight cycles or flight hours on the airplane since its first flight. (2) Where Airbus Service Bulletin A300-53-6177, dated May 20, 2015, specifies a compliance time ``from issuance of revision 04 of Service Bulletin No. A300-53-6111,'' or ``from issuance of Service Bulletin No. A300-53-6177,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (3) For Configuration 004 airplanes identified in Airbus Service Bulletin A300-53-6177, dated May 20, 2015: Within 6 months after the effective date of this AD, contact the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA), for corrective actions and accomplish all applicable corrective actions using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (i) Reporting At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD: Submit a report of the findings (both positive and negative) of each inspection required by paragraph (g) of this AD. Send the report to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com). (1) If the inspection was done on or after the effective date of this AD: Submit the report within 60 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 60 days after the effective date of this AD. (j) Optional Terminating Action Replacement of all lower frame feet between FR41 and FR46, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6176, dated May 20, 2015, terminates the repetitive inspections required by paragraph (g) of this AD. (k) 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: 425-227-1405; fax: 425-227-2125. Information may be emailed to: [email protected]. 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) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (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 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. (l) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015-0217, dated October 30, 2015, 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 Docket No. FAA- 2014-0143. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. [[Page 716]] (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A300-53-6176, dated May 20, 2015. (ii) Airbus Service Bulletin A300-53-6177, dated May 20, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; Internet: http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this 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/cfr/ibr-locations.html. Issued in Renton, Washington, on December 6, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-30117 Filed 1-3-17; 8:45 am] BILLING CODE 4910-13-P
![712 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations
75373–75377, 3 CFR, 2006 Comp., pp. 216– days, the FOIA Officer will include a DEPARTMENT OF TRANSPORTATION
200. notification of the requester’s right to
■ 2. Section 9301.5 is revised to read as seek dispute resolutions services from Federal Aviation Administration
follows: the Office of Government Information
Services. 14 CFR Part 39
§ 9301.5 Accessing records without
request * * * * * [Docket No. FAA–2014–0143; Directorate
Certain SIGAR records, including the (d) * * * Identifier 2012–NM–113–AD; Amendment
(1) Initiating appeals. Requesters not 39–18753; AD 2016–25–27]
agency’s Quarterly Report, audit reports,
satisfied with the FOIA Officer’s written
testimony, oversight plans, press RIN 2120–AA64
decision may request SIGAR’s FOIA
releases, other public issuances, and
Appellate Authority to review the Airworthiness Directives; Airbus
records that are required by 5 U.S.C.
decision. Appeals must be delivered in Airplanes
552(a)(2) to be made publicly available
writing within 90 days of the date of the
are available electronically from
decision and shall be addressed to the AGENCY: Federal Aviation
SIGAR’s homepage at http://
FOIA Appellate Authority, Office of Administration (FAA), Department of
www.sigar.mil. SIGAR encourages
Privacy, Records & Disclosure, Special Transportation (DOT).
requesters to visit its Web site before
Inspector General for Afghanistan ACTION: Final rule.
making a request for records under
Reconstruction, 2530 Crystal Drive,
§ 9301.6. SUMMARY: We are adopting a new
Arlington, VA 22202. As there may be
■ 3. In § 9301.6, paragraphs (c)(1)(ii), airworthiness directive (AD) for all
delays in mail delivery, it is advisable
(c)(3)(i), and (d)(1) are revised to read as to Fax appeals to (703) 601–3804 or Airbus Model A300 B4–603, B4–620,
follows: email to B4–622, B4–605R, B4–622R, F4–605R,
§ 9301.6 Requesting records. sigar.pentagon.gencoun.mbx.foia@ F4–622R, and C4–605R variant F
mail.mil. An appeal shall include a airplanes. This AD was prompted by
* * * * *
(c) * * * statement specifying the records that are reports of cracks in the frame base
(1) * * * the subject of the appeal and explaining fittings connecting the frame lower
(ii) Request denied. If the FOIA why the Appellate Authority should positions to the center wing box. This
Officer denies the request, in full or grant the appeal. AD requires repetitive detailed
part, the FOIA Officer shall provide the * * * * * inspections for cracking of the lower
requester written notice of the denial frame fittings of the frame foot, and
■ 4. In § 9301.8, paragraph (f)(3) is
together with the approximate number replacement with a new frame foot if
added to read as follows:
of pages of information withheld and cracking is found. This AD also
the exemption under which the § 9301.8 Fees in general. provides optional terminating action for
information was withheld. SIGAR will * * * * * the repetitive inspections. We are
indicate, if technically feasible, the (f) * * * issuing this AD to address the unsafe
amount of information deleted and the (3) SIGAR determines that unusual condition on these products.
exemption under which the deletion is circumstances apply to the processing of DATES: This AD is effective February 8,
made at the place in the record where a request, provides timely notice the 2017.
the deletion was made. SIGAR will also requester, and delay is excused for an The Director of the Federal Register
indicate the exemption under which a additional ten days, but SIGAR still fails approved the incorporation by reference
deletion is made on the released portion to respond within the timeframe of certain publications listed in this AD
of the record, unless including that established by the additional delay. This as of February 8, 2017.
indication would harm an interest provision applies only to search fees. ADDRESSES: For service information
protected by the exemptions. The notice However, the following exceptions shall identified in this final rule, contact
shall also describe the procedure for apply: Airbus SAS, Airworthiness Office—
filing an appeal. SIGAR will further (i) Notwithstanding § 9301.8(f)(3), if EAW, 1 Rond Point Maurice Bellonte,
notify the requester of their right to seek SIGAR determines that unusual 31707 Blagnac Cedex, France;
assistance from SIGAR’s FOIA Public circumstances apply and that telephone: +33 5 61 93 36 96; fax: +33
Liaison or dispute resolution services responding to the request requires the 5 61 93 44 51; email: account.airworth-
from the FOIA Public Liaison or the production of more than 5,000 pages, eas@airbus.com; Internet: http://
Office of Government Information SIGAR may continue to charge search www.airbus.com. You may view this
Services. fees, or duplication fees for requesters in referenced service information at the
* * * * * preferred status, for as long as FAA, Transport Airplane Directorate,
(3) * * * necessary, after timely written notice 1601 Lind Avenue SW., Renton, WA.
(i) In general. If the FOIA Officer has been made to the requester and For information on the availability of
determines that unusual circumstances SIGAR has discussed with the requester this material at the FAA, call 425–227–
exist, the FOIA Officer may extend for how the requester could effectively limit 1221. It is also available on the Internet
no more than ten days (except the scope of the request via written at http://www.regulations.gov by
Saturdays, Sundays and Federal mail, electronic mail, or telephone, or searching for and locating Docket No.
holidays) the time limits described in made three good-faith attempts to do so. FAA–2014–0143.
paragraph (c)(1) of this section by (ii) Notwithstanding § 9301.8(f)(3), if a
Examining the AD Docket
jstallworth on DSK7TPTVN1PROD with RULES
providing written notice of the court determines that exceptional
extension to the requester. The FOIA circumstances exist, SIGAR’s failure to You may examine the AD docket on
Officer shall include with the notice a comply with a time limit shall be the Internet at http://
brief statement of the reason for the excused for the length of time provided www.regulations.gov by searching for
extension and the date the FOIA Officer by the court order. and locating Docket No. FAA–2014–
expects to make the determination. If [FR Doc. 2016–30775 Filed 1–3–17; 8:45 am] 0143; or in person at the Docket
the extension goes beyond ten working BILLING CODE 3710–L9–P Management Facility between 9 a.m.
VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\04JAR1.SGM 04JAR1](https://thefederalregister.org/doc/82_FR_714/page/1.svg)
![Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations 713
and 5 p.m., Monday through Friday, 605R, F4–622R, and C4–605R variant F SNPRM) be extended from 30 to 60
except Federal holidays. The AD docket airplanes. The MCAI states: days. UPS stated that accomplishing the
contains this AD, the regulatory During accomplishment of Airbus Service inspection may occur many days before
evaluation, any comments received, and Bulletin (SB) A300–53–6111 (EASA AD the final task signoff (i.e., restoring
other information. The street address for 2012–0103), addressing detailed visual access due to other work in the area),
the Docket Office (telephone: 800–647– inspections of the lower frame fittings risking noncompliance with the 30-day
5527) is Docket Management Facility, between Frame (FR) 41 and FR46, a crack requirement.
U.S. Department of Transportation, was detected on one A300–600 aeroplane in We agree to extend the compliance
Docket Operations, M–30, West the area 2 of the foot of FR46 at junction
time for the reporting requirement in
radius level.
Building Ground Floor, Room W12–140, This frame, previously repaired due to a this AD to 60 days, because we have
1200 New Jersey Avenue SE., crack finding in the frame foot area 1, was determined that this longer compliance
Washington, DC 20590. not due to be inspected before reaching the time does not affect continued
FOR FURTHER INFORMATION CONTACT: Dan post-repair inspection threshold, i.e. 45,400 operational safety. We have changed
flight cycles since repair embodiment. paragraph (i) of this AD accordingly.
Rodina, Aerospace Engineer, Further investigation determined that the
International Branch, ANM–116, repairs specified in Airbus SB A300–53–6111 Request for Clarification of Compliance
Transport Airplane Directorate, FAA, were of limited effect to prevent cracking in Time
1601 Lind Avenue SW., Renton, WA the frame foot area 2.
98057–3356; telephone: 425–227–2125; This condition, if not detected and
Airbus asked that we clarify the
fax: 425–227–1149. corrected, could affect the structural integrity compliance time for the inspections
of the fuselage of all aeroplanes operated up specified in paragraph (g) of the
SUPPLEMENTARY INFORMATION: to the extended service goal (ESG). proposed AD (in the SNPRM). Airbus
Discussion As a temporary action and until an stated that unless Airbus Service
improvement of the existing repairs was Bulletin A300–53–6177, dated May 20,
We issued a supplemental notice of made available, EASA issued AD 2012–0229 2015, specifies differently, the
proposed rulemaking (SNPRM) to [AD * * *] to require a one-time detailed inspection thresholds should be
amend 14 CFR part 39 by adding an AD inspection (DET) of the frame feet that were counted from the first flight of the
repaired in accordance with Airbus SB
that would apply to all Airbus Model airplane, not from the effective date of
A300–53–6111, and the reporting of findings
A300 B4–603, B4–620, B4–622, B4– to Airbus. the AD. Airbus added that the
605R, B4–622R, F4–605R, F4–622R, and Since that [EASA] AD was issued, a compliance time provided in the
C4–605R variant F airplanes. The detailed study was performed resulting in the proposed AD could be confusing to
SNPRM published in the Federal development of a new inspection operators. Airbus also stated that for
Register on July 7, 2016 (81 FR 44241) programme. airplanes on which the inspections have
(‘‘the SNPRM’’). We preceded the Consequently, Airbus cancelled SB A300– not been done as of the effective date of
SNPRM with a notice of proposed 53–6111 and replaced it with SB A300–53– the AD, no grace period is provided,
rulemaking (NPRM) that published in 6177, introducing repetitive DET of the lower which is a burden on operators.
frame fittings between FR41 and FR46 for the
the Federal Register on March 19, 2014 We agree that clarification is
entire fleet. In addition to this new
(79 FR 15266) (‘‘the NPRM’’). The inspection programme, Airbus designed a necessary.
NPRM was prompted by reports of new frame foot which can be installed on We agree that the compliance time
cracks in the frame base fittings aeroplanes through Airbus SB A300–53– identified in the ‘‘Threshold’’ column of
connecting the frame lower positions to 6176. paragraph 1.E., ‘‘Compliance,’’ of Airbus
the center wing box. The NPRM For the reasons described above, this Service Bulletin A300–53–6177, dated
proposed to require repetitive detailed [EASA] AD supersedes EASA AD 2012–0103, May 20, 2015, refers to accumulated
inspections of the lower frame fittings, not retaining its requirements, and instead
flight cycles or flight hours on the
related investigative actions, and requires the new inspection programme for
the lower frame fittings. This [EASA] AD also airplane since its first flight, but only if
corrective actions if necessary. The Airbus Service Bulletin A300–53–6177,
introduces an optional terminating action for
SNPRM proposed to replace the the repetitive inspections required by the dated May 20, 2015, does not specify
proposed requirements in the NPRM [EASA] AD. differently. We redesignated paragraph
with new repetitive detailed inspections (h) in the SNPRM as paragraph (i) of this
for cracking of the lower frame fittings Corrective actions include replacing
any cracked lower frame fittings with a AD, and redesignated subsequent
of the frame foot, and replacement with paragraphs accordingly. We added
a new frame foot if cracking is found. new frame foot. You may examine the
MCAI in the AD docket on the Internet clarification of the compliance times for
The SNPRM also proposed to provide the thresholds in paragraph (h)(1) of this
optional terminating action for the at http://www.regulations.gov by
searching for and locating Docket No. AD.
repetitive inspections. We are issuing We acknowledge that a grace period
this AD to detect and correct cracking of FAA–2014–0143.
was not provided for all configurations.
the lower frame fittings, which could Comments We removed the grace period exception
result in reduced structural integrity of We gave the public the opportunity to language from paragraph (g) of the
the airplane. participate in developing this AD. The proposed AD (in the SNPRM) and
The European Aviation Safety Agency following presents the comments moved it to paragraph (h)(2) of this AD.
(EASA), which is the Technical Agent received on the SNPRM and the FAA’s Paragraph (h)(2) of this AD explains that
for the Member States of the European response to each comment. where grace periods specified in Airbus
jstallworth on DSK7TPTVN1PROD with RULES
Union, has issued EASA AD 2015–0217, Service Bulletin A300–53–6177, dated
dated October 30, 2015 (referred to after Request To Extend Compliance Time May 20, 2015, refer to the issue date of
this as the Mandatory Continuing for Reporting Requirement certain service information, those
Airworthiness Information, or ‘‘the United Parcel Service (UPS) asked compliance times are after the effective
MCAI’’), to correct an unsafe condition that the compliance time for submitting date of the AD. The exception in
on all Airbus Model A300 B4–603, B4– the inspection report specified in paragraph (h)(2) of this AD does not
620, B4–622, B4–605R, B4–622R, F4– paragraph (h) of the proposed AD (in the apply to compliance times specified as
VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\04JAR1.SGM 04JAR1](https://thefederalregister.org/doc/82_FR_714/page/2.svg)
![Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations 715
2. Is not a ‘‘significant rule’’ under the (h)(1) and (h)(2) of this AD: Perform a (1) Alternative Methods of Compliance
DOT Regulatory Policies and Procedures detailed inspection for cracking of the lower (AMOCs): The Manager, International
(44 FR 11034, February 26, 1979); frame fittings between frame (FR) 41 and Branch, ANM–116, Transport Airplane
3. Will not affect intrastate aviation in FR46 of the frame foot, and if any crack is Directorate, FAA, has the authority to
found, before further flight, replace with a approve AMOCs for this AD, if requested
Alaska; and new frame foot, in accordance with the using the procedures found in 14 CFR 39.19.
4. Will not have a significant Accomplishment Instructions of Airbus In accordance with 14 CFR 39.19, send your
economic impact, positive or negative, Service Bulletin A300–53–6177, dated May request to your principal inspector or local
on a substantial number of small entities 20, 2015, except as required by paragraph Flight Standards District Office, as
under the criteria of the Regulatory (h)(3) of this AD. Repeat the inspection appropriate. If sending information directly
Flexibility Act. thereafter at the applicable intervals specified to the International Branch, send it to ATTN:
in paragraph 1.E., ‘‘Compliance,’’ of Airbus Dan Rodina, Aerospace Engineer,
List of Subjects in 14 CFR Part 39 Service Bulletin A300–53–6177, dated May International Branch, ANM–116, Transport
Air transportation, Aircraft, Aviation 20, 2015. Airplane Directorate, FAA, 1601 Lind
safety, Incorporation by reference, (h) Service Information Exceptions Avenue SW., Renton, WA 98057–3356;
Safety. (1) Where the threshold identified in the telephone: 425–227–1405; fax: 425–227–
‘‘Threshold’’ column of paragraph 1.E., 2125. Information may be emailed to: 9-
Adoption of the Amendment ANM-116-AMOC-REQUESTS@faa.gov.
‘‘Compliance,’’ of Airbus Service Bulletin
Accordingly, under the authority A300–53–6177, dated May 20, 2015, specifies Before using any approved AMOC, notify
delegated to me by the Administrator, flight cycles or flight hours without your appropriate principal inspector, or
specifying from a repair, replacement, or last lacking a principal inspector, the manager of
the FAA amends 14 CFR part 39 as
inspection, the specified compliance time is the local flight standards district office/
follows: certificate holding district office. The AMOC
accumulated flight cycles or flight hours on
the airplane since its first flight. approval letter must specifically reference
PART 39—AIRWORTHINESS this AD.
(2) Where Airbus Service Bulletin A300–
DIRECTIVES (2) Contacting the Manufacturer: For any
53–6177, dated May 20, 2015, specifies a
compliance time ‘‘from issuance of revision requirement in this AD to obtain corrective
■ 1. The authority citation for part 39 actions from a manufacturer, the action must
04 of Service Bulletin No. A300–53–6111,’’
continues to read as follows: or ‘‘from issuance of Service Bulletin No. be accomplished using a method approved
Authority: 49 U.S.C. 106(g), 40113, 44701. A300–53–6177,’’ this AD requires by the Manager, International Branch, ANM–
compliance within the specified compliance 116, Transport Airplane Directorate, FAA; or
§ 39.13 [Amended] time after the effective date of this AD. the European Aviation Safety Agency
■ 2. The FAA amends § 39.13 by adding (3) For Configuration 004 airplanes (EASA); or Airbus’s EASA Design
identified in Airbus Service Bulletin A300– Organization Approval (DOA). If approved by
the following new airworthiness 53–6177, dated May 20, 2015: Within 6 the DOA, the approval must include the
directive (AD): months after the effective date of this AD, DOA-authorized signature.
2016–25–27 Airbus: Amendment 39–18753; contact the Manager, International Branch, (3) Reporting Requirements: A federal
Docket No. FAA–2014–0143; Directorate ANM–116, Transport Airplane Directorate, agency may not conduct or sponsor, and a
Identifier 2012–NM–113–AD. FAA; or the European Aviation Safety person is not required to respond to, nor
Agency (EASA); or Airbus’s EASA Design shall a person be subject to a penalty for
(a) Effective Date Organization Approval (DOA), for corrective failure to comply with a collection of
This AD is effective February 8, 2017. actions and accomplish all applicable information subject to the requirements of
corrective actions using a method approved the Paperwork Reduction Act unless that
(b) Affected ADs by the Manager, International Branch, ANM– collection of information displays a current
None. 116, Transport Airplane Directorate, FAA; or valid OMB Control Number. The OMB
EASA; or Airbus’s EASA DOA. Control Number for this information
(c) Applicability
(i) Reporting collection is 2120–0056. Public reporting for
This AD applies to Airbus Model A300 B4–
this collection of information is estimated to
603, B4–620, B4–622, B4–605R, B4–622R, At the applicable time specified in
be approximately 5 minutes per response,
F4–605R, F4–622R, and C4–605R variant F paragraph (i)(1) or (i)(2) of this AD: Submit
including the time for reviewing instructions,
airplanes; certificated in any category; all a report of the findings (both positive and
completing and reviewing the collection of
serial numbers. negative) of each inspection required by
information. All responses to this collection
paragraph (g) of this AD. Send the report to
(d) Subject of information are mandatory. Comments
Airbus Service Bulletin Reporting Online
Air Transport Association (ATA) of Application on Airbus World (https:// concerning the accuracy of this burden and
America Code 53, Fuselage. w3.airbus.com). suggestions for reducing the burden should
(1) If the inspection was done on or after be directed to the FAA at: 800 Independence
(e) Reason Ave. SW., Washington, DC 20591, Attn:
the effective date of this AD: Submit the
This AD was prompted by reports of cracks report within 60 days after the inspection. Information Collection Clearance Officer,
in the frame base fittings connecting the (2) If the inspection was done before the AES–200.
frame lower positions to the center wing box. effective date of this AD: Submit the report (l) Related Information
We are issuing this AD to detect and correct within 60 days after the effective date of this
cracking of the lower frame fittings, which AD. Refer to Mandatory Continuing
could result in reduced structural integrity of Airworthiness Information (MCAI) EASA AD
the airplane. (j) Optional Terminating Action 2015–0217, dated October 30, 2015, for
Replacement of all lower frame feet related information. This MCAI may be
(f) Compliance between FR41 and FR46, in accordance with found in the AD docket on the Internet at
Comply with this AD within the the Accomplishment Instructions of Airbus http://www.regulations.gov by searching for
jstallworth on DSK7TPTVN1PROD with RULES
compliance times specified, unless already Service Bulletin A300–53–6176, dated May and locating Docket No. FAA–2014–0143.
done. 20, 2015, terminates the repetitive (m) Material Incorporated by Reference
inspections required by paragraph (g) of this
(g) Repetitive Inspections and Replacement AD. (1) The Director of the Federal Register
At the applicable time specified in approved the incorporation by reference
paragraph 1.E., ‘‘Compliance,’’ of Airbus (k) Other FAA AD Provisions (IBR) of the service information listed in this
Service Bulletin A300–53–6177, dated May The following provisions also apply to this paragraph under 5 U.S.C. 552(a) and 1 CFR
20, 2015, except as required by paragraphs AD: part 51.
VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\04JAR1.SGM 04JAR1](https://thefederalregister.org/doc/82_FR_714/page/4.svg)
![716 Federal Register / Vol. 82, No. 2 / Wednesday, January 4, 2017 / Rules and Regulations
(2) You must use this service information ADDRESSES: For service information some MRBs may have reduced blade
as applicable to do the actions required by identified in this final rule, contact fatigue resistance due to repair by
this AD, unless this AD specifies otherwise. Robinson Helicopter Company, 2901 blending out corrosion in the area of the
(i) Airbus Service Bulletin A300–53–6176, Airport Drive, Torrance, CA 90505; crack site radius. The proposed
dated May 20, 2015.
(ii) Airbus Service Bulletin A300–53–6177,
telephone (310) 539–0508; fax (310) requirements were intended to prevent
dated May 20, 2015. 539–5198; or at http:// an MRB fatigue crack, which could lead
(3) For service information identified in www.robinsonheli.com. You may review to MRB failure and subsequent loss of
this AD, contact Airbus SAS, Airworthiness a copy of the referenced service helicopter control.
Office—EAW, 1 Rond Point Maurice information at the FAA, Office of the
Bellonte, 31707 Blagnac Cedex, France;
Comments
Regional Counsel, Southwest Region,
telephone: +33 5 61 93 36 96; fax: +33 5 61 10101 Hillwood Pkwy, Room 6N–321, After our NPRM (81 FR 33609, May
93 44 51; email: account.airworth-eas@ Fort Worth, TX 76177. It is also 27, 2016) was published, we received a
airbus.com; Internet: http://www.airbus.com. available on the Internet at http:// comment from one commenter.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
www.regulations.gov by searching for Request
1601 Lind Avenue SW., Renton, WA. For and locating Docket No. FAA–2016–
0733. Robinson requested we change the
information on the availability of this
material at the FAA, call 425–227–1221.
applicability of the AD for part number
Examining the AD Docket (P/N) C016–7 from ‘‘Revision N/C, A
(5) You may view this service information
that is incorporated by reference at the You may examine the AD docket on through Z, and AA through AE’’ to
National Archives and Records the Internet at http:// ‘‘Revision AA through AE.’’ Robinson
Administration (NARA). For information on www.regulations.gov by searching for stated that P/N C016–7 did not exist
the availability of this material at NARA, call and locating Docket No. FAA–2016– until Revision AA and suggested that
202–741–6030, or go to: http:// 0733; or in person at the Docket some technicians may wrongfully apply
www.archives.gov/federal-register/cfr/ibr- the proposed AD to P/N C016–5
locations.html.
Operations Office between 9 a.m. and 5
p.m., Monday through Friday, except Revisions W thru Z.
Issued in Renton, Washington, on Federal holidays. The AD docket We agree and have revised the AD
December 6, 2016. contains this AD, any incorporated-by- accordingly.
Dionne Palermo, reference service information, the FAA’s Determination
Acting Manager, Transport Airplane economic evaluation, any comments
Directorate, Aircraft Certification Service. We have reviewed the relevant
received, and other information. The
[FR Doc. 2016–30117 Filed 1–3–17; 8:45 am] information, considered the comment
street address for the Docket Operations
received, and determined that an unsafe
BILLING CODE 4910–13–P Office (phone: 800–647–5527) is U.S.
condition exists and is likely to exist or
Department of Transportation, Docket
develop on other products of these same
Operations Office, M–30, West Building
DEPARTMENT OF TRANSPORTATION type designs and that air safety and the
Ground Floor, Room W12–140, 1200
public interest require adopting the AD
New Jersey Avenue SE., Washington,
Federal Aviation Administration requirements as proposed with the
DC 20590.
change previously described. This
14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: Eric change is consistent with the intent of
Schrieber, Aviation Safety Engineer, Los the proposals in the NPRM (81 FR
[Docket No. FAA–2016–0733; Directorate Angeles Aircraft Certification Office, 33609, May 27, 2016) and will not
Identifier 2015–SW–040–AD; Amendment Transport Airplane Directorate, FAA, increase the economic burden on any
39–18762; AD 2016–26–04] 3960 Paramount Blvd., Lakewood, operator nor increase the scope of the
California 90712; telephone (562) 627– AD.
RIN 2120–AA64
5348; email eric.schrieber@faa.gov.
SUPPLEMENTARY INFORMATION:
Related Service Information Under 1
Airworthiness Directives; Robinson CFR Part 51
Helicopter Company Helicopters Discussion
We reviewed Robinson R44 Service
AGENCY: Federal Aviation On May 27, 2016, at 81 FR 33609, the Bulletin SB–89, dated March 30, 2015
Administration (FAA), DOT. Federal Register published our notice of (SB–89), for Model R44 and R44 II
ACTION: Final rule. proposed rulemaking (NPRM), which helicopters and Robinson R66 Service
proposed to amend 14 CFR part 39 by Bulletin SB–13, dated March 30, 2015
SUMMARY: We are adopting a new adding an AD that would apply to (SB–13), for Model R66 helicopters. SB–
airworthiness directive (AD) for Robinson Model R44 and R44 II 89 and SB–13 provide a one-time
Robinson Helicopter Company helicopters with an MRB part number procedure to inspect each MRB for
(Robinson) Model R44, R44 II, and R66 (P/N) C016–7, Revision N/C, A through cracks, corrosion, and damage that may
helicopters. This AD requires inspecting Z, and AA through AE; and Model R66 indicate a crack. If there is a crack,
the main rotor blade (MRB). This AD helicopters with an MRB P/N F016–2, corrosion, or any damage, SB–89 and
was prompted by a determination that Revision A through E. The NPRM SB–13 specify removing the MRB from
some MRBs may have reduced blade proposed to require a one-time visual service and contacting Robinson.
thickness due to blending out corrosion. inspection of the MRB for a crack, Otherwise, SB–89 and SB–13 describe
The actions are intended to prevent the corrosion, dent, nick, and scratch and procedures to smooth the transition at
jstallworth on DSK7TPTVN1PROD with RULES
unsafe condition on these products. either altering the MRB or removing it the chord increase of each MRB to
DATES: This AD is effective February 8, from service. reduce the stress concentration.
2017. The NPRM was prompted by a report This service information is reasonably
The Director of the Federal Register of a fatigue crack on a Model R44 II available because the interested parties
approved the incorporation by reference helicopter at the MRB trailing edge that have access to it through their normal
of certain documents listed in this AD had grown to reach the blade spar. The course of business or by the means
as of February 8, 2017. FAA subsequently determined that identified in the ADDRESSES section.
VerDate Sep<11>2014 15:22 Jan 03, 2017 Jkt 241001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\04JAR1.SGM 04JAR1](https://thefederalregister.org/doc/82_FR_714/page/5.svg)
Document Created: 2017-01-04 00:29:22
Document Modified: 2017-01-04 00:29:22
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective February 8, 2017. | |
| 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. | |
| FR Citation | 82 FR 712 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR