82 FR 39351 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 159 (August 18, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 159 (August 18, 2017)
| Page Range | 39351-39355 | |
| FR Document | 2017-16359 |
[Federal Register Volume 82, Number 159 (Friday, August 18, 2017)] [Rules and Regulations] [Pages 39351-39355] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-16359] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9052; Product Identifier 2016-NM-080-AD; Amendment 39-18983; AD 2017-16-06] 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 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of failure of an aft hinge bolt assembly in the nose landing gear (NLG) aft doors. This AD requires replacement of the aft hinge bolt assembly in the left and right NLG aft doors, with new aft hinge bolt assemblies. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective September 22, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 22, 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 account.airworth-eas@airbus.com; Internet http:// [[Page 39352]] www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 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-2016- 9052. 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- 9052; 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 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 Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227- 1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. The NPRM published in the Federal Register on August 30, 2016 (81 FR 59546) (``the NPRM''). The NPRM was prompted by reports of failure of an aft hinge bolt assembly in the NLG aft doors. The NPRM proposed to require replacement of the aft hinge bolt assembly in the left and right NLG aft doors, with new aft hinge bolt assemblies. We are issuing this AD to prevent failure of an aft hinge bolt assembly in an NLG aft door while the airplane is in flight, which could lead to an in-flight loss of an NLG aft door, and damage to 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 2016-0100, dated May 24, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. The MCAI states: An occurrence has been reported of failure of a nose landing gear (NLG) door aft hinge bolt assembly, Part Number (P/N) A53612600000. The result of laboratory investigations revealed that the aft hinge bolt rupture was initiated by fatigue crack development in the under head radius of the bolt, due to the lack of radius roll over and in combination with a non-optimised design. This condition, if not detected and corrected, could lead to in- flight loss of an aft NLG door, possibly resulting in damage to the aeroplane and injury to persons on the ground. Prompted by these findings, Airbus developed a new design aft hinge bolt assembly P/N A53612713000, introduced as Airbus modification (mod) 13741, to replace the existing bolt P/N A53612600000. Since the introduction of that mod, additional stress calculations demonstrated that the new bolt assembly, P/N A53612713000, cannot sustain fatigue loads up to the design Limit of Validity (LOV) of the affected aeroplanes. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A300-53-0397, SB A310-53-2144 and SB A300-53- 6186, to provide instructions for the repetitive replacement of the affected post-mod 13741 P/N A53612713000 aft hinge bolts. For the reasons described above, this [EASA] AD requires the replacement of all P/N A53612600000 aft hinge bolt assemblies, installed on the left hand (LH) and right hand (RH) NLG aft doors, with post-mod 13741 P/N A53612713000 aft hinge bolt assemblies, and, subsequently, the implementation of a life limit for those new bolt assemblies. 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-2016- 9052. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Withdraw the NPRM FedEx stated it does not agree that the proposed hinge bolt replacement is necessary, asserting that the severity of a failed condition does not equate to an unsafe condition on the airplane. FedEx explained that in the last 22 years of flight operations, it has not had a departure of the NLG door, nor has it seen any cracking of the aft hinge bolt. From this statement, we infer that FedEx requested we withdraw the NPRM. We disagree with this request. Airbus has records of multiple instances of hinge bolt failures. Failure of an aft hinge bolt assembly in an NLG aft door while the airplane is in flight could lead to an in- flight loss of an NLG aft door, and damage to the airplane. We have not changed this AD in this regard. Request To Allow Option for Repetitive Inspections FedEx requested that a repetitive non-destructive test (NDT) technique be allowed as an option to replacing the affected bolts. FedEx stated that a routine NDT inspection would be best suited for this condition and that the affected bolts should only be replaced as an on-condition action. Further, FedEx stated that the proposed requirement to replace all affected bolts will be a financial burden on operators. FedEx also pointed out that the two bolts required for each airplane are $2,300, and these bolts will be required to be replaced every 10,000 flight cycles (approximately every 10 years). FedEx further requested that the FAA petition the EASA to revise the Airbus service information to permit the repetitive inspection as an option to the required bolt replacement. We disagree with the commenter's request. The intent of this AD is to regularly replace the affected hinge bolt with a new one. The bolt loading and fatigue spectrum is complex, and the manufacturer is not able to substantiate a fatigue life to support a repeat inspection program. Therefore, we have made no changes to this AD in this regard. However, under the provisions of paragraph (k)(1) of this AD, we will consider requests for approval of an alternative method of compliance (AMOC) if sufficient data are submitted to substantiate that the change would provide an acceptable level of safety. Request To Remove the Requirement To Replace Aft Hinge Bolts United Parcel Service (UPS) requested that we revise the proposed AD to remove the requirement to replace aft hinge bolts. UPS contended that the more appropriate method for implementation of the repetitive 10,000-flight-cycle replacement of the hinge bolt assembly would be through a maintenance program revision, or incorporation into the Safe Life Airworthiness Limitation Items (SL ALI)--Part 1. Therefore, UPS recommended that we delete the proposed hinge bolt replacement, and [[Page 39353]] instead coordinate with EASA to revise the SL ALI to include the hinge bolt assembly. We disagree with the commenter's request. Only parts that are identified as a safe life part are incorporated into the SL ALI. The specified hinge bolt does not meet the Airbus Airworthiness Limitations Section (ALS) Part 1 criteria for a safe life part. The hinge bolt does not have fatigue testing or demonstrated fatigue life analysis, which is required for safe life parts. We have not changed this AD in this regard. Request To Combine Certain Service Information UPS requested that, if its request to revise the proposed AD to remove the hinge assembly replacement is unacceptable to the FAA, we revise paragraph (h)(3) of this proposed AD to require removal and installation of a new bolt using only Airbus Service Bulletin A300-53- 6182 and not list Airbus Service Bulletin A300-53-6186. UPS explained that the final result of the proposed AD is the replacement of the bolt in every case; however, Airbus Service Bulletin A300-53-6186 specifies doing an inspection of the bolt part number in addition to the replacement and is an added burden to the operator given the location of the identifying mark and the difficulty accessing that mark. We disagree with the commenter's request because paragraphs (g) and (h) of this AD and the corresponding service information are necessary to distinguish between two different actions with different compliance times:Paragraph (g) of this AD and corresponding service information for the introduction of the bolt's new design. Paragraph (h) of this AD and corresponding service bulletin for regular bolt replacement, which includes an inspection for verification if the proper bolt part number was installed. While it might be difficult for operators to identify the part number of the bolt when it is installed on the aircraft, the bolt is scheduled to be removed so it should not be difficult to verify that the correct part was installed. We have not changed this AD in this regard. Request To Update Illustrated Parts Catalog (IPC) To Show the Post- Modification Part Number UPS requested that the FAA coordinate with EASA and Airbus to ensure that the IPC is updated to show only the post-modification part number prior to the AD being issued. UPS was concerned that an outdated IPC creates opportunities for installation of the original, non- compliant bolt assembly. We infer that UPS was also requesting that we delay publication of the final rule pending revision of the IPC. We disagree with this request. Airbus has informed the FAA that the IPC is scheduled to be revised. However, we do not consider that delaying this action until after the release of the manufacturer's revised IPC is warranted, since sufficient information currently exists in this AD and the required service information to address the identified unsafe condition. We have not changed this AD in this regard. Clarification of Corrective Action We have clarified the corrective actions in the introductory text of paragraph (h) of this AD by referring to paragraph (k)(2) of this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed the following Airbus service information. Airbus Service Bulletin A300-53-0396, dated November 25, 2015. Airbus Service Bulletin A300-53-6182, dated November 17, 2015. Airbus Service Bulletin A310-53-2142, dated November 17, 2015. This service information describes procedures for replacement of the aft hinge bolt assemblies in the left and right NLG aft doors, with new aft hinge bolt assemblies. These documents are distinct since they apply to different airplane models and configurations. We also reviewed the following Airbus service information. Airbus Service Bulletin A300-53-0397, dated January 18, 2016. Airbus Service Bulletin A300-53-6186, dated January 18, 2016. Airbus Service Bulletin A310-53-2144, dated January 18, 2016. This service information describes procedures for replacement of the aft hinge bolt assemblies in the left and right NLG aft doors, with new aft hinge bolt assemblies. The replacement includes an inspection to verify if the proper bolt part number was installed and repair if the proper bolt part number was not installed. These documents are distinct since they apply to different airplane models and configurations. 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 157 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Replacement........................ 9 work-hours x $85 per hour $2,000 $2,765 $434,105 = $765. ---------------------------------------------------------------------------------------------------------------- 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 [[Page 39354]] that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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; 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): 2017-16-06 Airbus: Amendment 39-18983; Docket No. FAA-2016-9052; Product Identifier 2016-NM-080-AD. (a) Effective Date This AD is effective September 22, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus airplanes identified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes. (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (3) Model A300 B4-605R and B4-622R airplanes. (4) Model A300 F4-605R and F4-622R airplanes. (5) Model A300 C4-605R Variant F airplanes. (6) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of failure of an aft hinge bolt assembly in the nose landing gear (NLG) aft doors. We are issuing this AD to prevent failure of an aft hinge bolt assembly in an NLG aft door while the airplane is in flight, which could lead to an in- flight loss of an NLG aft door, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement of Aft Hinge Bolt Assemblies Having Part Number (P/N) A53612600000 Before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later: Replace each aft hinge bolt assembly having P/N A53612600000 on the left and right NLG aft doors, with a new hinge bolt assembly having P/N A53612713000, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (1) Airbus Service Bulletin A300-53-0396, dated November 25, 2015. (2) Airbus Service Bulletin A310-53-2142, dated November 17, 2015. (3) Airbus Service Bulletin A300-53-6182, dated November 17, 2015. (h) Replacement of Aft Hinge Bolt Assemblies Having P/N A53612713000 Within 10,000 flight cycles after modification of an airplane as required by paragraph (g) of this AD: Replace each aft hinge bolt assembly having P/N A53612713000 on the left and right NLG aft doors, with a new aft hinge bolt assembly having P/N A53612713000 on the left and right NLG aft doors, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, except where the service information specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD specifies to contact Airbus for instructions, before further flight repair using the procedure in paragraph (k)(2) of this AD. Repeat the replacement thereafter at intervals not to exceed 10,000 flight cycles. (1) Airbus Service Bulletin A300-53-0397, dated January 18, 2016. (2) Airbus Service Bulletin A310-53-2144, dated January 18, 2016. (3) Airbus Service Bulletin A300-53-6186, dated January 18, 2016. (i) Parts Installation Prohibition (P/N A53612600000) After modification of an airplane NLG aft door as required by paragraph (g) of this AD, do not install an aft hinge bolt assembly having P/N A53612600000 on any NLG aft door of that airplane. (j) Parts Installation Limitation (P/N A53612713000) After removal of an aft hinge bolt assembly having P/N A53612713000 from an airplane NLG aft door, as required by paragraph (h) of this AD, do not install an aft hinge bolt assembly having that part number on that airplane unless it is a new aft hinge bolt assembly. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. (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 Section, Transport Standards Branch, 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) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in [[Page 39355]] an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0100, dated May 24, 2016, 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-2016-9052. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. (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. (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 A300-53-0396, dated November 25, 2015. (ii) Airbus Service Bulletin A300-53-0397, dated January 18, 2016. (iii) Airbus Service Bulletin A300-53-6182, dated November 17, 2015. (iv) Airbus Service Bulletin A300-53-6186, dated January 18, 2016. (v) Airbus Service Bulletin A310-53-2142, dated November 17, 2015. (vi) Airbus Service Bulletin A310-53-2144, dated January 18, 2016. (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 account.airworth-eas@airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 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 July 26, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-16359 Filed 8-17-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 159 / Friday, August 18, 2017 / Rules and Regulations 39351
(n) Exceptions to Service Information procedures and tests must be done to comply 1601 Lind Avenue SW., Renton, WA. For
Specifications with this AD; any procedures or tests that are information on the availability of this
Subtask 271257–832–006–001 of Airbus not identified as RC are recommended. Those material at the FAA, call 425–227–1221.
Service Bulletin A320–27–1257, Revision 01, procedures and tests that are not identified (7) You may view this service information
dated January 1, 2017, includes incorrect as RC may be deviated from using accepted that is incorporated by reference at the
instructions. This AD requires that those methods in accordance with the operator’s National Archives and Records
instructions be followed as specified in maintenance or inspection program without Administration (NARA). For information on
paragraphs (n)(1) and (n)(2) of this AD. obtaining approval of an AMOC, provided the availability of this material at NARA, call
(1) For Subtask 271257–832–006–001, the procedures and tests identified as RC can 202–741–6030, or go to: http://
instruction ‘‘(b)’’: If SEC C 126 software P/N be done and the airplane can be put back in www.archives.gov/federal-register/cfr/ibr-
B372CAM0104 is found, no further action is an airworthy condition. Any substitutions or locations.html.
required by this AD. changes to procedures or tests identified as
RC require approval of an AMOC. Issued in Renton, Washington, on June 29,
(2) For Subtask 271257–832–006–001, 2017.
instruction ‘‘(c)’’: If SEC C 122 software P/N (q) Special Flight Permits Michael Kaszycki,
B372CAM0101, SEC C 124 software P/N
Special flight permits, as described in Acting Manager, Transport Airplane
B372CAM0102, or SEC C 125 software P/N
Section 21.197 and Section 21.199 of the Directorate, Aircraft Certification Service.
B372CAM0103 is found, do corrective
Federal Aviation Regulations (14 CFR 21.197
actions using a method approved by the [FR Doc. 2017–14471 Filed 8–17–17; 8:45 am]
and 21.199), are not allowed.
Manager, International Branch, ANM–116, BILLING CODE 4910–13–P
Transport Airplane Directorate, FAA; or (r) Related Information
EASA; or Airbus’s EASA DOA. (1) Refer to Mandatory Continuing
(o) Credit for Previous Actions Airworthiness Information (MCAI) EASA DEPARTMENT OF TRANSPORTATION
Airworthiness Directive 2016–0056, dated
This paragraph provides credit for the
actions required by paragraph (i) of this AD,
March 18, 2016, for related information. This Federal Aviation Administration
MCAI may be found in the AD docket on the
if those actions were performed before the
Internet at http://www.regulations.gov by 14 CFR Part 39
effective date of this AD using the applicable
searching for and locating Docket No. FAA–
service information specified in paragraph [Docket No. FAA–2016–9052; Product
2016–9508.
(o)(1) or (o)(2) of this AD. Identifier 2016–NM–080–AD; Amendment
(2) For more information about this AD,
(1) For airplanes that have received Airbus 39–18983; AD 2017–16–06]
contact Sanjay Ralhan, Aerospace Engineer,
modification 39429 (installation of SEC
International Branch, ANM–116, Transport
hardware C P/N B372CAM0100) in RIN 2120–AA64
Airplane Directorate, FAA, 1601 Lind
production: Airbus Service Bulletin A320–
Avenue SW., Renton, WA 98057–3356;
27–1252, dated November 6, 2015.
telephone 425–227–1405; fax 425–227–1149. Airworthiness Directives; Airbus
(2) For airplanes that have not received (3) Service information identified in this Airplanes
Airbus modification 39429 in production: AD that is not incorporated by reference is
Airbus Service Bulletin A320–27–1257, AGENCY: Federal Aviation
available at the addresses specified in
dated December 18, 2015. paragraphs (s)(5) and (s)(6) of this AD. Administration (FAA), Department of
(p) Other FAA AD Provisions
Transportation (DOT).
(s) Material Incorporated by Reference ACTION: Final rule.
The following provisions also apply to this (1) The Director of the Federal Register
AD: approved the incorporation by reference SUMMARY: We are adopting a new
(1) Alternative Methods of Compliance (IBR) of the service information listed in this airworthiness directive (AD) for all
(AMOCs): The Manager, International paragraph under 5 U.S.C. 552(a) and 1 CFR
Branch, ANM–116, Transport Airplane Airbus Model A300 series airplanes;
part 51. Model A300 B4–600, B4–600R, and F4–
Directorate, FAA, has the authority to (2) You must use this service information
approve AMOCs for this AD, if requested as applicable to do the actions required by
600R series airplanes, and Model A300
using the procedures found in 14 CFR 39.19. this AD, unless this AD specifies otherwise. C4–605R Variant F airplanes
In accordance with 14 CFR 39.19, send your (3) The following service information was (collectively called Model A300–600
request to your principal inspector or local approved for IBR on September 22, 2017. series airplanes); and Model A310 series
Flight Standards District Office, as (i) Airbus Service Bulletin A320–27–1252, airplanes. This AD was prompted by
appropriate. If sending information directly Revision 01, dated February 18, 2016. reports of failure of an aft hinge bolt
to the International Branch, send it to the (ii) Airbus Service Bulletin A320–27–1257, assembly in the nose landing gear (NLG)
attention of the person identified in Revision 01, dated January 1, 2017.
paragraph (r)(2) of this AD. Information may aft doors. This AD requires replacement
(4) The following service information was
be emailed to: 9-ANM-116-AMOC- of the aft hinge bolt assembly in the left
approved for IBR on November 20, 2015 (80
REQUESTS@faa.gov. Before using any FR 68429, November 5, 2015). and right NLG aft doors, with new aft
approved AMOC, notify your appropriate (i) Airbus A318/A319/A320/A321 hinge bolt assemblies. We are issuing
principal inspector, or lacking a principal Temporary Revision TR572, Issue 1.0, dated this AD to address the unsafe condition
inspector, the manager of the local flight August 13, 2015, to the Airbus A318/A319/ on these products.
standards district office/certificate holding A320/A321 Airplane Flight Manual. DATES: This AD is effective September
district office. The AMOC approval letter (ii) Reserved.
must specifically reference this AD.
22, 2017.
(5) For service information identified in
(2) Contacting the Manufacturer: For any this AD, contact Airbus, Airworthiness
The Director of the Federal Register
requirement in this AD to obtain corrective Office—EIAS, 1 Rond Point Maurice approved the incorporation by reference
actions from a manufacturer, the action must Bellonte, 31707 Blagnac Cedex, France; of certain publications listed in this AD
be accomplished using a method approved telephone +33 5 61 93 36 96; fax +33 5 61 as of September 22, 2017.
by the Manager, International Branch, ANM– 93 44 51; email account.airworth-eas@ ADDRESSES: For service information
116, Transport Airplane Directorate, FAA; or
mstockstill on DSK30JT082PROD with RULES
airbus.com; Internet http://www.airbus.com. identified in this final rule, contact
EASA; or Airbus’s EASA DOA. If approved You may view this referenced service Airbus SAS, Airworthiness Office—
by the DOA, the approval must include the information at the FAA, Transport Airplane
DOA-authorized signature. Directorate, 1601 Lind Avenue SW., Renton,
EAW, 1 Rond Point Maurice Bellonte,
(3) Required for Compliance (RC): Except WA. For information on the availability of 31707 Blagnac Cedex, France; telephone
as required by paragraph (n) of this AD: If this material at the FAA, call 425–227–1221. +33 5 61 93 36 96; fax +33 5 61 93 44
any service information contains procedures (6) You may view this service information 51; email account.airworth-eas@
or tests that are identified as RC, those at the FAA, Transport Airplane Directorate, airbus.com; Internet http://
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www.airbus.com. You may view this dated May 24, 2016 (referred to after departure of the NLG door, nor has it
referenced service information at the this as the Mandatory Continuing seen any cracking of the aft hinge bolt.
FAA, Transport Standards Branch, 1601 Airworthiness Information, or ‘‘the From this statement, we infer that
Lind Avenue SW., Renton, WA. For MCAI’’), to correct an unsafe condition FedEx requested we withdraw the
information on the availability of this for all Airbus Model A300 series NPRM. We disagree with this request.
material at the FAA, call 425–227–1221. airplanes; Model A300 B4–600, B4– Airbus has records of multiple instances
It is also available on the Internet at 600R, and F4–600R series airplanes, and of hinge bolt failures. Failure of an aft
http://www.regulations.gov by searching Model A300 C4–605R Variant F hinge bolt assembly in an NLG aft door
for and locating Docket No. FAA–2016– airplanes (collectively called Model while the airplane is in flight could lead
9052. A300–600 series airplanes); and Model to an in-flight loss of an NLG aft door,
A310 series airplanes. The MCAI states: and damage to the airplane. We have
Examining the AD Docket not changed this AD in this regard.
An occurrence has been reported of failure
You may examine the AD docket on of a nose landing gear (NLG) door aft hinge Request To Allow Option for Repetitive
the Internet at http:// bolt assembly, Part Number (P/N) Inspections
www.regulations.gov by searching for A53612600000. The result of laboratory
and locating Docket No. FAA–2016– investigations revealed that the aft hinge bolt FedEx requested that a repetitive non-
9052; or in person at the Docket rupture was initiated by fatigue crack destructive test (NDT) technique be
Management Facility between 9 a.m. development in the under head radius of the allowed as an option to replacing the
and 5 p.m., Monday through Friday, bolt, due to the lack of radius roll over and affected bolts. FedEx stated that a
except Federal holidays. The AD docket in combination with a non-optimised design. routine NDT inspection would be best
This condition, if not detected and suited for this condition and that the
contains this AD, the regulatory corrected, could lead to in-flight loss of an aft
evaluation, any comments received, and affected bolts should only be replaced as
NLG door, possibly resulting in damage to an on-condition action. Further, FedEx
other information. The street address for the aeroplane and injury to persons on the
the Docket Office (telephone 800–647– stated that the proposed requirement to
ground.
5527) is Docket Management Facility, Prompted by these findings, Airbus replace all affected bolts will be a
U.S. Department of Transportation, developed a new design aft hinge bolt financial burden on operators. FedEx
Docket Operations, M–30, West assembly P/N A53612713000, introduced as also pointed out that the two bolts
Building Ground Floor, Room W12–140, Airbus modification (mod) 13741, to replace required for each airplane are $2,300,
1200 New Jersey Avenue SE., the existing bolt P/N A53612600000. Since and these bolts will be required to be
the introduction of that mod, additional replaced every 10,000 flight cycles
Washington, DC 20590. stress calculations demonstrated that the new (approximately every 10 years). FedEx
FOR FURTHER INFORMATION CONTACT: Dan bolt assembly, P/N A53612713000, cannot further requested that the FAA petition
Rodina, Aerospace Engineer, sustain fatigue loads up to the design Limit the EASA to revise the Airbus service
International Section, Transport of Validity (LOV) of the affected aeroplanes.
To address this potential unsafe condition,
information to permit the repetitive
Standards Branch, FAA, 1601 Lind inspection as an option to the required
Avenue SW., Renton, WA 98057–3356; Airbus issued Service Bulletin (SB) A300–
53–0397, SB A310–53–2144 and SB A300– bolt replacement.
telephone 425–227–2125; fax 425–227– We disagree with the commenter’s
53–6186, to provide instructions for the
1149. repetitive replacement of the affected post- request. The intent of this AD is to
SUPPLEMENTARY INFORMATION: mod 13741 P/N A53612713000 aft hinge regularly replace the affected hinge bolt
bolts. with a new one. The bolt loading and
Discussion For the reasons described above, this fatigue spectrum is complex, and the
We issued a notice of proposed [EASA] AD requires the replacement of all manufacturer is not able to substantiate
rulemaking (NPRM) to amend 14 CFR P/N A53612600000 aft hinge bolt assemblies, a fatigue life to support a repeat
part 39 by adding an AD that would installed on the left hand (LH) and right hand
(RH) NLG aft doors, with post-mod 13741 P/
inspection program. Therefore, we have
apply to all Airbus Model A300 series made no changes to this AD in this
N A53612713000 aft hinge bolt assemblies,
airplanes; Model A300 B4–600, B4– and, subsequently, the implementation of a regard. However, under the provisions
600R, and F4–600R series airplanes, and life limit for those new bolt assemblies. of paragraph (k)(1) of this AD, we will
Model A300 C4–605R Variant F consider requests for approval of an
airplanes (collectively called Model You may examine the MCAI in the alternative method of compliance
A300–600 series airplanes); and Model AD docket on the Internet at http:// (AMOC) if sufficient data are submitted
A310 series airplanes. The NPRM www.regulations.gov by searching for to substantiate that the change would
published in the Federal Register on and locating Docket No. FAA–2016– provide an acceptable level of safety.
August 30, 2016 (81 FR 59546) (‘‘the 9052.
NPRM’’). The NPRM was prompted by Request To Remove the Requirement To
Comments Replace Aft Hinge Bolts
reports of failure of an aft hinge bolt
assembly in the NLG aft doors. The We gave the public the opportunity to United Parcel Service (UPS) requested
NPRM proposed to require replacement participate in developing this AD. The that we revise the proposed AD to
of the aft hinge bolt assembly in the left following presents the comments remove the requirement to replace aft
and right NLG aft doors, with new aft received on the NPRM and the FAA’s hinge bolts. UPS contended that the
hinge bolt assemblies. We are issuing response to each comment. more appropriate method for
this AD to prevent failure of an aft hinge Request To Withdraw the NPRM implementation of the repetitive 10,000-
bolt assembly in an NLG aft door while flight-cycle replacement of the hinge
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the airplane is in flight, which could FedEx stated it does not agree that the bolt assembly would be through a
lead to an in-flight loss of an NLG aft proposed hinge bolt replacement is maintenance program revision, or
door, and damage to the airplane. necessary, asserting that the severity of incorporation into the Safe Life
The European Aviation Safety Agency a failed condition does not equate to an Airworthiness Limitation Items (SL
(EASA), which is the Technical Agent unsafe condition on the airplane. FedEx ALI)—Part 1. Therefore, UPS
for the Member States of the European explained that in the last 22 years of recommended that we delete the
Union, has issued EASA AD 2016–0100, flight operations, it has not had a proposed hinge bolt replacement, and
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![39354 Federal Register / Vol. 82, No. 159 / Friday, August 18, 2017 / Rules and Regulations
that is likely to exist or develop on (b) Affected ADs specified in paragraph (h)(1), (h)(2), or (h)(3)
products identified in this rulemaking None. of this AD specifies to contact Airbus for
action. instructions, before further flight repair using
(c) Applicability the procedure in paragraph (k)(2) of this AD.
This AD is issued in accordance with
This AD applies to Airbus airplanes Repeat the replacement thereafter at intervals
authority delegated by the Executive not to exceed 10,000 flight cycles.
Director, Aircraft Certification Service, identified in paragraphs (c)(1) through (c)(6)
of this AD, certificated in any category, all (1) Airbus Service Bulletin A300–53–0397,
as authorized by FAA Order 8000.51C. manufacturer serial numbers. dated January 18, 2016.
In accordance with that order, issuance (1) Model A300 B2–1A, B2–1C, B2K–3C, (2) Airbus Service Bulletin A310–53–2144,
of ADs is normally a function of the B2–203, B4–2C, B4–103, and B4–203 dated January 18, 2016.
Compliance and Airworthiness airplanes. (3) Airbus Service Bulletin A300–53–6186,
Division, but during this transition (2) Model A300 B4–601, B4–603, B4–620, dated January 18, 2016.
period, the Executive Director has and B4–622 airplanes. (i) Parts Installation Prohibition (P/N
delegated the authority to issue ADs (3) Model A300 B4–605R and B4–622R A53612600000)
airplanes.
applicable to transport category (4) Model A300 F4–605R and F4–622R After modification of an airplane NLG aft
airplanes to the Director of the System airplanes. door as required by paragraph (g) of this AD,
Oversight Division. (5) Model A300 C4–605R Variant F do not install an aft hinge bolt assembly
airplanes. having P/N A53612600000 on any NLG aft
Regulatory Findings door of that airplane.
(6) Model A310–203, –204, –221, –222,
We determined that this AD will not –304, –322, –324, and –325 airplanes. (j) Parts Installation Limitation (P/N
have federalism implications under (d) Subject A53612713000)
Executive Order 13132. This AD will After removal of an aft hinge bolt assembly
not have a substantial direct effect on Air Transport Association (ATA) of
America Code 53, Fuselage. having P/N A53612713000 from an airplane
the States, on the relationship between NLG aft door, as required by paragraph (h) of
the national government and the States, (e) Reason this AD, do not install an aft hinge bolt
or on the distribution of power and This AD was prompted by reports of failure assembly having that part number on that
responsibilities among the various of an aft hinge bolt assembly in the nose airplane unless it is a new aft hinge bolt
levels of government. landing gear (NLG) aft doors. We are issuing assembly.
For the reasons discussed above, I this AD to prevent failure of an aft hinge bolt (k) Other FAA AD Provisions
certify that this AD: assembly in an NLG aft door while the
airplane is in flight, which could lead to an The following provisions also apply to this
1. Is not a ‘‘significant regulatory AD:
action’’ under Executive Order 12866; in-flight loss of an NLG aft door, and damage
to the airplane. (1) Alternative Methods of Compliance
2. Is not a ‘‘significant rule’’ under the (AMOCs): The Manager, International
DOT Regulatory Policies and Procedures (f) Compliance Section, Transport Standards Branch, FAA,
(44 FR 11034, February 26, 1979); Comply with this AD within the has the authority to approve AMOCs for this
3. Will not affect intrastate aviation in compliance times specified, unless already AD, if requested using the procedures found
Alaska; and done. in 14 CFR 39.19. In accordance with 14 CFR
4. Will not have a significant 39.19, send your request to your principal
(g) Replacement of Aft Hinge Bolt inspector or local Flight Standards District
economic impact, positive or negative, Assemblies Having Part Number (P/N) Office, as appropriate. If sending information
on a substantial number of small entities A53612600000 directly to the International Section, send it
under the criteria of the Regulatory to the attention of the person identified in
Before the accumulation of 10,000 total
Flexibility Act. flight cycles since first flight of the airplane, paragraph (l)(2) of this AD. Information may
List of Subjects in 14 CFR Part 39 or within 2,000 flight cycles after the be emailed to: 9-ANM-116-AMOC–
effective date of this AD, whichever occurs REQUESTS@faa.gov. Before using any
Air transportation, Aircraft, Aviation later: Replace each aft hinge bolt assembly approved AMOC, notify your appropriate
safety, Incorporation by reference, having P/N A53612600000 on the left and principal inspector, or lacking a principal
Safety. right NLG aft doors, with a new hinge bolt inspector, the manager of the local flight
assembly having P/N A53612713000, in standards district office/certificate holding
Adoption of the Amendment accordance with the Accomplishment district office.
Accordingly, under the authority Instructions of the applicable service (2) Contacting the Manufacturer: For any
delegated to me by the Administrator, information identified in paragraph (g)(1), requirement in this AD to obtain corrective
(g)(2), or (g)(3) of this AD. actions from a manufacturer, the action must
the FAA amends 14 CFR part 39 as be accomplished using a method approved
(1) Airbus Service Bulletin A300–53–0396,
follows: dated November 25, 2015. by the Manager, International Section,
(2) Airbus Service Bulletin A310–53–2142, Transport Standards Branch, FAA; or the
PART 39—AIRWORTHINESS dated November 17, 2015. European Aviation Safety Agency (EASA); or
DIRECTIVES (3) Airbus Service Bulletin A300–53–6182, Airbus’s EASA Design Organization
dated November 17, 2015. Approval (DOA). If approved by the DOA,
■ 1. The authority citation for part 39 the approval must include the DOA-
continues to read as follows: (h) Replacement of Aft Hinge Bolt authorized signature.
Assemblies Having P/N A53612713000 (3) Required for Compliance (RC): If any
Authority: 49 U.S.C. 106(g), 40113, 44701.
Within 10,000 flight cycles after service information contains procedures or
§ 39.13 [Amended] modification of an airplane as required by tests that are identified as RC, those
paragraph (g) of this AD: Replace each aft procedures and tests must be done to comply
■ 2. The FAA amends § 39.13 by adding with this AD; any procedures or tests that are
hinge bolt assembly having P/N
the following new airworthiness
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A53612713000 on the left and right NLG aft not identified as RC are recommended. Those
directive (AD): doors, with a new aft hinge bolt assembly procedures and tests that are not identified
2017–16–06 Airbus: Amendment 39–18983; having P/N A53612713000 on the left and as RC may be deviated from using accepted
Docket No. FAA–2016–9052; Product right NLG aft doors, in accordance with the methods in accordance with the operator’s
Identifier 2016–NM–080–AD. Accomplishment Instructions of the maintenance or inspection program without
applicable service information specified in obtaining approval of an AMOC, provided
(a) Effective Date paragraph (h)(1), (h)(2), or (h)(3) of this AD, the procedures and tests identified as RC can
This AD is effective September 22, 2017. except where the service information be done and the airplane can be put back in
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![Federal Register / Vol. 82, No. 159 / Friday, August 18, 2017 / Rules and Regulations 39355
an airworthy condition. Any substitutions or DEPARTMENT OF TRANSPORTATION Docket Operations Office (phone: 800–
changes to procedures or tests identified as 647–5527) is U.S. Department of
RC require approval of an AMOC. Federal Aviation Administration Transportation, Docket Operations
(l) Related Information Office, M–30, West Building Ground
14 CFR Part 39 Floor, Room W12–140, 1200 New Jersey
(1) Refer to Mandatory Continuing Avenue SE., Washington, DC 20590.
Airworthiness Information (MCAI) EASA [Docket No. FAA–2017–0068; Product
Identifier 2014–SW–076–AD; Amendment FOR FURTHER INFORMATION CONTACT:
Airworthiness Directive 2016–0100, dated
May 24, 2016, for related information. This
39–18981; AD 2017–16–04] David Hatfield, Aviation Safety
MCAI may be found in the AD docket on the RIN 2120–AA64
Engineer, Safety Management Section,
Internet at http://www.regulations.gov by Rotorcraft Standards Branch, FAA,
searching for and locating Docket No. FAA– Airworthiness Directives; Romtex 10101 Hillwood Pkwy., Fort Worth, TX
2016–9052. Anjou Aeronautique (Romtex) Torso 76177; telephone (817) 222–5116; email
(2) For more information about this AD, Restraint Systems david.hatfield@faa.gov.
contact Dan Rodina, Aerospace Engineer, SUPPLEMENTARY INFORMATION:
AGENCY: Federal Aviation
International Section, Transport Standards
Administration (FAA), DOT. Discussion
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone 425– ACTION: Final rule. On February 17, 2017, at 82 FR 10971,
227–2125; fax 425–227–1149. the Federal Register published our
SUMMARY: We are adopting a new notice of proposed rulemaking (NPRM),
(m) Material Incorporated by Reference airworthiness directive (AD) for Romtex which proposed to amend 14 CFR part
(1) The Director of the Federal Register torso restraint systems (restraint 39 by adding an AD that would apply
approved the incorporation by reference systems) installed on but not limited to to Romtex restraint systems with a
(IBR) of the service information listed in this Airbus Helicopters Model AS350B2, rotary buckle sub-assembly (buckle
paragraph under 5 U.S.C. 552(a) and 1 CFR AS350B3, EC130B4, EC130T2, and assembly) with a part number and serial
part 51. AS355NP helicopters. This AD requires number listed in Romtex Service
(2) You must use this service information replacing certain restraint system Bulletin No. 358SB–14–101, Revision 1,
as applicable to do the actions required by buckles. This AD was prompted by a dated December 12, 2014. These
this AD, unless this AD specifies otherwise. report of several restraint system buckle restraint systems are installed on, but
(i) Airbus Service Bulletin A300–53–0396, knobs breaking. The actions of this AD not limited to, Airbus Helicopters
dated November 25, 2015. are intended to correct an unsafe Model AS350B2, AS350B3, EC130B4,
(ii) Airbus Service Bulletin A300–53–0397, condition on these products. EC130T2, and AS355NP helicopters.
dated January 18, 2016. DATES: This AD is effective September The NPRM proposed to require
(iii) Airbus Service Bulletin A300–53– 22, 2017. inspecting the buckle assembly to
6182, dated November 17, 2015. The Director of the Federal Register determine whether the straps release,
(iv) Airbus Service Bulletin A300–53– approved the incorporation by reference marking the seat as inoperative if the
6186, dated January 18, 2016. of a certain document listed in this AD buckle fails to release the straps, and
(v) Airbus Service Bulletin A310–53–2142, as of September 22, 2017. replacing the buckle assembly within
dated November 17, 2015.
ADDRESSES: For service information 180 hours time-in-service (TIS). The
(vi) Airbus Service Bulletin A310–53–
identified in this final rule, contact NPRM also proposed to prohibit
2144, dated January 18, 2016.
Romtex Anjou Aeronautique, Strada installing the affected buckle assemblies
(3) For service information identified in
Livezii nr. 98, 550042, Sibiu, Romania; on any helicopter. The proposed
this AD, contact Airbus SAS, Airworthiness
telephone +40 269 243 918; email requirements were intended to prevent
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; seatbelts@anjouaero.com. You may a restraint system strap from failing to
telephone +33 5 61 93 36 96; fax +33 5 61 review the referenced service release from the buckle, preventing
93 44 51; email account.airworth-eas@ information at the FAA, Office of the occupants from exiting the helicopter
airbus.com; Internet http://www.airbus.com. Regional Counsel, Southwest Region, during an emergency.
(4) You may view this service information 10101 Hillwood Pkwy., Room 6N–321, The NPRM was prompted by AD No.
at the FAA, Transport Standards Branch, Fort Worth, TX 76177. It is also 2014–0279, dated December 19, 2014,
1601 Lind Avenue SW., Renton, WA. For available on the Internet at http:// issued by EASA, which is the Technical
information on the availability of this www.regulations.gov by searching for Agent for the Member States of the
material at the FAA, call 425–227–1221. and locating Docket No. FAA–2017– European Union, to correct an unsafe
(5) You may view this service information 0068. condition for Romtex Model 358 torso
that is incorporated by reference at the restraint systems installed on Airbus
Examining the AD Docket Helicopters Model EC130T2, AS350B2,
National Archives and Records
Administration (NARA). For information on You may examine the AD docket on and AS350B3 helicopters. EASA advises
the availability of this material at NARA, call the Internet at http:// that ruptures have occurred on the
202–741–6030, or go to: http:// www.regulations.gov by searching for upper side (knob) of several rotary
www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2017– buckles installed on these restraint
locations.html. 0068; or in person at the Docket systems. EASA states the material used
Operations Office between 9 a.m. and 5 in two batches of the buckle assembly
Issued in Renton, Washington, on July 26,
p.m., Monday through Friday, except were altered by a supplier, resulting in
2017.
mstockstill on DSK30JT082PROD with RULES
Federal holidays. The AD docket a specification different from the
Jeffrey E. Duven, contains this AD, the European Aviation approved design data. The EASA AD
Director, System Oversight Division, Aircraft Safety Agency (EASA) AD, any states that this condition could prevent
Certification Service. incorporated-by-reference service the release of the restraint system straps
[FR Doc. 2017–16359 Filed 8–17–17; 8:45 am] information, the economic evaluation, as intended after an emergency landing.
BILLING CODE 4910–13–P any comments received, and other To address this unsafe condition, the
information. The street address for the EASA AD requires inspecting the buckle
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Document Created: 2017-08-18 07:40:30
Document Modified: 2017-08-18 07:40:30
| 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 September 22, 2017. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227- 1149. | |
| FR Citation | 82 FR 39351 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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