82 FR 29363 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 124 (June 29, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 124 (June 29, 2017)
| Page Range | 29363-29368 | |
| FR Document | 2017-13407 |
[Federal Register Volume 82, Number 124 (Thursday, June 29, 2017)] [Rules and Regulations] [Pages 29363-29368] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-13407] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. ======================================================================== Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Rules and Regulations [[Page 29363]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9573; Directorate Identifier 2016-NM-149-AD; Amendment 39-18938; AD 2017-13-08] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2015-23-13, for all Airbus Model A318 and A319 series airplanes, Model A320-211, - 212, -214, -231, -232, and -233 airplanes, and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. AD 2015-23-13 required modification of the pin programming of the flight warning computer (FWC) to activate the stop rudder input warning (SRIW) logic; and an inspection to determine the part numbers of the FWC and the flight augmentation computer (FAC), and replacement of the FWC and FAC if necessary. This new AD, for certain airplanes, also requires accomplishment of additional modification instructions to install the minimum FWC and FAC configuration compatible with SRIW activation. This AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 3, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 3, 2017. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of December 29, 2015 (80 FR 73099, November 24, 2015). ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 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. 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-2016- 9573. 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- 9573; 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 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2015-23-13, Amendment 39-18330 (80 FR 73099, November 24, 2015) (``AD 2015-23-13''). AD 2015-23-13 applied to all Airbus Model A318 and A319 series airplanes, Model A320-211, -212, - 214, -231, -232, and -233 airplanes, and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. The NPRM published in the Federal Register on February 15, 2017 (82 FR 10721) (``the NPRM''). The NPRM was prompted by a determination that, for certain airplanes, additional modification instructions must be accomplished to allow installation of the minimum FWC and FAC configuration compatible with SRIW activation. The NPRM proposed to continue to require modification of the pin programming of the FWC to activate the SRIW logic; and an inspection to determine the part numbers of the FWC and the FAC, and replacement of the FWC and FAC if necessary. The NPRM also proposed, for certain airplanes, to also require accomplishment of additional modification instructions to install the minimum FWC and FAC configuration compatible with SRIW activation. We are issuing this AD to prevent detachment of the vertical tail plane and consequent loss of control 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 Airworthiness Directive 2016-0132, dated July 5, 2016; corrected July 20, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A318 and A319 series airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states: During design reviews that were conducted following safety recommendations related to in-service incidents and one accident on another aircraft type, it has been determined that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. This condition, if not corrected, could lead to in-flight detachment of the vertical tail plane, possibly resulting in loss of control of the aeroplane. To address this unsafe condition, Airbus developed modifications within the flight augmentation computer (FAC) to reduce the vertical tail plane stress and to activate a conditional aural warning within the flight warning computer (FWC) to further protect against pilot induced rudder doublets. Consequently, EASA issued AD 2014-0217 (later revised) [which corresponds to FAA AD 2015-23-13] to require installation and activation of the stop rudder input warning (SRIW) logic. In addition, that [EASA] AD [[Page 29364]] required upgrades of the FAC and FWC, to introduce the SRIW logic and SRIW aural capability, respectively. After modification, the [EASA] AD prohibited (re)installation of certain Part Number (P/N) FWC and FAC. Since EASA AD 2014-0217R1 was issued, Airbus made available additional modification instructions that, for certain aeroplanes, must be accomplished to allow installation of the minimum FWC and FAC configuration compatible with SRIW activation. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2014-0217R1, which is superseded, and includes reference to modification instructions, which must be accomplished on certain aeroplanes. This [EASA] AD is republished to remove a typographical error in Appendix 1 [of the EASA AD]. 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- 9573. 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 for Technical Details Mr. Geoffrey Barrance stated that the public disclosure in the NPRM did not provide sufficient technical details and disclosure relative to the unsafe condition; and that, presumably, the actions required by this proposed AD are to improve the protection provided by the SRIW logic. Mr. Barrance noted that the purpose of publication in the Federal Register is to provide public disclosure. We infer the commenter is requesting that we provide additional technical details. We do not agree with the commenter's request. The technical details associated with correcting the unsafe condition were already provided in the previously published AD, AD 2015-23-13. That AD and all service information that was incorporated by reference in AD 2015-23-13 is posted on the public docket in the Federal Docket Management System and is available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-0251. This superseding AD only mandates accomplishment of additional modification instructions to ensure design compatibility. We have not revised this AD in this regard. Request for Review of Design Approval Process and Compliance Time Determination Mr. Geoffrey Barrance asserted that this rulemaking action is a result of failure of design, development, oversight and approval processes at the EASA and the FAA. Mr. Barrance asserted that the FAA must do a comprehensive review of these processes and evaluate the extent that the flying public has been exposed to risks due to delayed processes in releasing this AD. We do not agree with Mr. Geoffrey Barrance's comments. Mr. Barrance has submitted no data to substantiate his claims. This rulemaking action simply supersedes a previous AD in order to mandate accomplishment of additional modification instructions to ensure design compatibility. Furthermore, we and our bilateral partner, EASA, work closely with Airbus to ensure that design solutions are certificated based on applicable airworthiness regulations prior to mandating those solutions to mitigate safety risks. We also ensure that all appropriate instructions and parts are available at the appropriate time to comply with AD requirements. As a component of our safety management system, we continuously evaluate our certification system and procedures and improve them when problems are found. We have not revised this AD in this regard. Request for Compliance Time Review The Air Line Pilots Association, International (ALPA) stated that it agrees with the NPRM, but requested that we revisit the compliance timeframe to ensure it is aligned with the intent of the AD. The EASA has determined the compliance times based on the overall risk to the fleet, including the severity of the failure and the likelihood of the failure's occurrence. The FAA and EASA worked with Airbus to ensure that all appropriate action(s) are taken at appropriate times to mitigate the risk to the fleet. We have not changed this AD in this regard. Request for Correction of Typographical Error Jetblue Airways (Jetblue) requested that we correct a typographical error in paragraph (i)(10) of the NPRM. Jetblue stated that it should be ``FWC H2-F7,'' not ``FWC H-F7.'' We agree with the commenter's request and have revised this AD accordingly. Request for an Alternative Method of Compliance (AMOC) Jetblue requested that we include an AMOC for FWC standard H2-F9D (P/N 350E053021818) in this AD. We do not agree to include an AMOC in this AD because certain later approved parts are already addressed in paragraph (l) of this AD. To clarify, FWCs approved after March 5, 2015, are an approved method of compliance with the requirements of paragraph (h) or (j) of this AD, provided the requirements specified in paragraphs (l)(1) and (l)(2) of this AD are met. We have not changed this AD in this regard. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously and minor editorial changes. We have determined that these 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 Airbus has issued Service Bulletin A320-22-1480, Revision 02, dated March 30, 2015, and Service Bulletin A320-22-1480, Revision 03, dated October 13, 2015. This service information describes procedures for modifying the pin programming to activate the SRIW logic. These documents are distinct due to editorial revisions. Airbus has also issued the following service information. The service information describes procedures for replacing FWCs and FACs. These documents are distinct since they apply to different airplane configurations and software packages. Airbus Service Bulletin A320-22-1375, dated January 15, 2014. Airbus Service Bulletin A320-22-1427, Revision 05, including Appendix 01, dated November 24, 2014. Airbus Service Bulletin A320-22-1447, Revision 03, dated April 21, 2015. Airbus Service Bulletin A320-22-1454, dated February 12, 2014. Airbus Service Bulletin A320-22-1461, Revision 07, including Appendix 01, dated March 23, 2015. Airbus Service Bulletin A320-22-1502, dated November 14, 2014. Airbus Service Bulletin A320-22-1539, Revision 01, dated February 24, 2016. Airbus Service Bulletin A320-22-1553, dated March 21, 2016. Airbus Service Bulletin A320-22-1554, dated April 19, 2016. Airbus Service Bulletin A320-31-1414, Revision 03, dated September 15, 2014. This service information is reasonably available because the interested parties [[Page 29365]] 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 will affect 1,032 airplanes of U.S. registry. The actions required by AD 2015-23-13, and retained in this AD take about 3 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2015-23-13 is $255 per product. We also estimate that it would take about 3 work-hours per product to comply with the basic requirements of this AD. 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 $263,160, or $255 per product. In addition, we estimate that any necessary follow-on actions will take about 6 work-hours (3 work-hours for an FWC and 3 work-hours for an FAC), and require parts costing $88,000 (FAC), for a cost of $88,510 per product. We have no way of determining the number of aircraft that might need these actions. 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; 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 removing Airworthiness Directive (AD) 2015-23-13, Amendment 39-18330 (80 FR 73099, November 24, 2015), and adding the following new AD: 2017-13-08 Airbus: Amendment 39-18938; Docket No. FAA-2016-9573; Directorate Identifier 2016-NM-149-AD. (a) Effective Date This AD is effective August 3, 2017. (b) Affected ADs This AD replaces AD 2015-23-13, Amendment 39-18330 (80 FR 73099, November 24, 2015) (``AD 2015-23-13''). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318-111, -112, -121, and -122 airplanes. (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 22, Auto Flight; 31, Instruments. (e) Reason This AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. Exceeding allowable load limits could result in detachment of the vertical tail plane. We are issuing this AD to prevent detachment of the vertical tail plane and consequent loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Pin Programming Modification, With New Service Information This paragraph restates the requirements of paragraph (g) of AD 2015-23-13, with new service information. Within 48 months after December 29, 2015 (the effective date of AD 2015-23-13), modify the pin programming to activate the stop rudder input warning (SRIW) logic, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-22-1480, Revision 02, dated March 30, 2015; or Airbus Service Bulletin A320-22-1480, Revision 03, dated October 13, 2015. As of the effective date of this AD, use only Airbus Service Bulletin A320-22-1480, Revision 03, dated October 13, 2015. (h) Retained Inspection To Determine Part Numbers (P/Ns), Flight Warning Computer (FWC) and Flight Augmentation Computer (FAC) Replacement, With New Replacement Part Numbers This paragraph restates the requirements of paragraph (h) of AD 2015-23-13, with new replacement part numbers. Prior to or concurrently with the actions required by paragraph (g) of this AD: Inspect the part numbers of the FWC and the FAC installed on the airplane. If any FWC or FAC having a part number identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, is installed on an airplane, prior to or concurrently with the actions required by paragraph (g) of this AD, replace all affected FWCs and FACs with a unit having a part number identified in figure 1 to paragraph (h)(3) of this AD, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraph (i) of this AD. As of the effective date of this AD, use only figure 1 to paragraph (h)(3) of this AD to identify the replacement part numbers. (1) Paragraphs (h)(1)(i) through (h)(1)(xvii) of this AD identify FWCs having part numbers that are non-compatible with the SRIW activation required by paragraph (g) of this AD. (i) 350E017238484 (H1-D1). (ii) 350E053020303 (H2-E3). (iii) 350E016187171 (C5). (iv) 350E053020404 (H2-E4). (v) 350E017248685 (H1-D2). (vi) 350E053020606 (H2-F2). (vii) 350E017251414 (H1-E1). (viii) 350E053020707 (H2-F3). (ix) 350E017271616 (H1-E2). (x) 350E053021010 (H2-F3P). (xi) 350E018291818 (H1-E3CJ). (xii) 350E053020808 (H2-F4). (xiii) 350E018301919 (H1-E3P). (xiv) 350E053020909 (H2-F5). (xv) 350E018312020 (H1-E3Q). (xvi) 350E053021111 (H2-F6). (xvii) 350E053020202 (H2-E2). [[Page 29366]] (2) Paragraphs (h)(2)(i) through (h)(2)(xxxiv) of this AD identify FACs having part numbers that are non-compatible with the SRIW activation required by paragraph (g) of this AD. (i) B397AAM0202. (ii) B397BAM0101. (iii) B397BAM0512. (iv) B397AAM0301. (v) B397BAM0202. (vi) B397BAM0513. (vii) B397AAM0302. (viii) B397BAM0203. (ix) B397BAM0514. (x) B397AAM0303. (xi) B397BAM0305. (xii) B397BAM0515. (xiii) B397AAM0404. (xiv) B397BAM0406. (xv) B397BAM0616. (xvi) B397AAM0405. (xvii) B397BAM0407. (xviii) B397BAM0617. (xix) B397AAM0506. (xx) B397BAM0507. (xxi) B397BAM0618. (xxii) B397AAM0507. (xxiii) B397BAM0508. (xxiv) B397BAM0619. (xxv) B397AAM0508. (xxvi) B397BAM0509. (xxvii) B397BAM0620. (xxviii) B397AAM0509. (xxix) B397BAM0510. (xxx) B397CAM0101. (xxxi) B397AAM0510. (xxxii) B397BAM0511. (xxxiii) B397CAM0102. (xxxiv) Soft P/N G2856AAA01 installed on hard P/N C13206AA00. (3) As of the effective date of this AD, figure 1 to paragraph (h)(3) of this AD identifies the FACs and FWCs having the part numbers that are compatible with SRIW activation required by paragraph (g) of this AD. BILLING CODE 4910-13-P [GRAPHIC] [TIFF OMITTED] TR29JN17.000 [[Page 29367]] BILLING CODE 4910-13-C (i) Retained Service Information for Actions Required by Paragraph (h) of This AD, With New Service Information This paragraph restates the requirements of paragraph (i) of AD 2015-23-13, with new service information. Do the actions required by paragraph (h) of this AD in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (i)(1) through (i)(10) of this AD. (1) Airbus Service Bulletin A320-22-1375, dated January 15, 2014 (FAC 621 hard B). (2) Airbus Service Bulletin A320-22-1427, Revision 05, including Appendix 01, dated November 24, 2014 (FAC 622 hard B). (3) Airbus Service Bulletin A320-22-1447, Revision 03, dated April 21, 2015 (FAC CAA02 hard C). (4) Airbus Service Bulletin A320-22-1454, dated February 12, 2014 (FAC CAA02). (5) Airbus Service Bulletin A320-22-1461, Revision 07, including Appendix 01, dated March 23, 2015 (FAC 623 hard B). (6) Airbus Service Bulletin A320-22-1502, dated November 14, 2014 (FAC CAA02). (7) Airbus Service Bulletin A320-22-1539, Revision 01, dated February 24, 2016 (FAC CAA03). (8) Airbus Service Bulletin A320-22-1553, dated March 21, 2016 (FAC B624). (9) Airbus Service Bulletin A320-22-1554, dated April 19, 2016 (FAC CAA03). (10) Airbus Service Bulletin A320-31-1414, Revision 03, dated September 15, 2014 (FWC H2-F7). (j) Retained Exclusion From Actions Required by Paragraphs (g) and (h) of This AD, With No Changes This paragraph restates the requirements of paragraph (j) of AD 2015-23-13, with no changes. An airplane on which Airbus Modification 154473 has been embodied in production is excluded from the requirements of paragraphs (g) and (h) of this AD, provided that within 30 days after December 29, 2015 (the effective date of AD 2015-23-13), an inspection of the part numbers of the FWC and the FAC installed on the airplane is done to determine that no FWC having a part number listed in paragraph (h)(1) of this AD, and no FAC having a part number listed in paragraph (h)(2) of this AD, has been installed on that airplane since date of manufacture. A review of airplane maintenance records is acceptable in lieu of this inspection if the part numbers of the FWC and FAC can be conclusively determined from that review. If any FWC or FAC having a part number identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, is installed on a post Airbus Modification 154473 airplane: Within 30 days after December 29, 2015, do the replacement required by paragraph (h) of this AD. (k) Retained Parts Installation Prohibitions, With New Requirements This paragraph restates the parts installation prohibitions specified in paragraph (k) of AD 2015-23-13, with new requirements. (1) After modification of an airplane as required by paragraphs (g), (h), or (j) of this AD: Do not install on that airplane any FWC having a part number listed in paragraph (h)(1) of this AD or any FAC having a part number listed in paragraph (h)(2) of this AD. (2) For an airplane that does not have a FWC having a part number listed in paragraph (h)(1) of this AD and does not have a FAC having a part number listed in paragraph (h)(2) of this AD: As of the effective date of this AD, do not install a FWC having a part number listed in paragraph (h)(1) of this AD or a FAC having a part number listed in paragraph (h)(2) of this AD. (l) Retained Later Approved Parts, With a Different Effective Date This paragraph restates the requirements of paragraph (l) of AD 2015-23-13, with a different effective date. Installation of a version (part number) of the FWC or FAC approved after March 5, 2015 (the effective date of European Aviation Safety Agency (EASA) AD 2014-0217R1), is an approved method of compliance with the requirements of paragraph (h) or (j) of this AD, provided the requirements specified in paragraphs (l)(1) and (l)(2) of this AD are met. (1) The version (part number) must be approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA Design Organization Approval (DOA). (2) The installation must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (m) Credit for Previous Actions (1) This paragraph restates the credit provided by paragraph (m)(1) of AD 2015-23-13. This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before December 29, 2015 (the effective date of AD 2015- 23-13) using the service information specified in paragraphs (m)(1)(i) or (m)(1)(ii) of this AD. (i) Airbus Service Bulletin A320-22-1480, dated July 9, 2014. (ii) Airbus Service Bulletin A320-22-1480, Revision 01, dated February 6, 2015. (2) This paragraph restates the credit provided by paragraph (m)(2) of AD 2015-23-13. This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before December 29, 2015 (the effective date of AD 2015- 23-13) using the applicable Airbus service information identified in paragraphs (m)(2)(i) through (m)(2)(xviii) of this AD. (i) Airbus Service Bulletin A320-22-1427, dated January 25, 2013. (ii) Airbus Service Bulletin A320-22-1427, Revision 01, dated July 30, 2013. (iii) Airbus Service Bulletin A320-22-1427, Revision 02, dated October 14, 2013. (iv) Airbus Service Bulletin A320-22-1427, Revision 03, dated November 8, 2013. (v) Airbus Service Bulletin A320-22-1427, Revision 04, dated February 11, 2014. (vi) Airbus Service Bulletin A320-22-1447, dated October 18, 2013. (vii) Airbus Service Bulletin A320-22-1447, Revision 01, dated September 18, 2014. (viii) Airbus Service Bulletin A320-22-1447, Revision 02, dated December 2, 2014. (ix) Airbus Service Bulletin A320-22-1461, dated October 31, 2013. (x) Airbus Service Bulletin A320-22-1461, Revision 01, dated February 25, 2014. (xi) Airbus Service Bulletin A320-22-1461, Revision 02, dated April 30, 2014. (xii) Airbus Service Bulletin A320-22-1461, Revision 03, dated July 17, 2014. (xiii) Airbus Service Bulletin A320-22-1461, Revision 04, dated September 15, 2014. (xiv) Airbus Service Bulletin A320-22-1461, Revision 05, dated November 13, 2014. (xv) Airbus Service Bulletin A320-22-1461, Revision 06, dated January 21, 2015. (xvi) Airbus Service Bulletin A320-31-1414, dated December 19, 2012. (xvii) Airbus Service Bulletin A320-31-1414, Revision 01, dated March 21, 2013. (xviii) Airbus Service Bulletin A320-31-1414, Revision 02, dated July 30, 2013. (3) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-22- 1539, dated December 28, 2015. (n) 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 the attention of the person identified in paragraph (o)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2015-23-13, are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 EASA; or Airbus's EASA 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 [[Page 29368]] 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 an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0132, dated July 5, 2016; corrected July 20, 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-2016-9573. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(5) and (p)(6) of this AD. (p) 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. (3) The following service information was approved for IBR on August 3, 2017. (i) Airbus Service Bulletin A320-22-1480, Revision 03, dated October 13, 2015. (ii) Airbus Service Bulletin A320-22-1539, Revision 01, dated February 24, 2016. (iii) Airbus Service Bulletin A320-22-1553, dated March 21, 2016. (iv) Airbus Service Bulletin A320-22-1554, dated April 19, 2016. (4) The following service information was approved for IBR on December 29, 2015 (80 FR 73099, November 24, 2015). (i) Airbus Service Bulletin A320-22-1375, dated January 15, 2014. (ii) Airbus Service Bulletin A320-22-1427, Revision 05, including Appendix 01, dated November 24, 2014. (iii) Airbus Service Bulletin A320-22-1447, Revision 03, dated April 21, 2015. (iv) Airbus Service Bulletin A320-22-1454, dated February 12, 2014. (v) Airbus Service Bulletin A320-22-1461, Revision 07, including Appendix 01, dated March 23, 2015. (vi) Airbus Service Bulletin A320-22-1480, Revision 02, dated March 30, 2015. (vii) Airbus Service Bulletin A320-22-1502, dated November 14, 2014. (viii) Airbus Service Bulletin A320-31-1414, Revision 03, dated September 15, 2014. (5) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 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. (6) 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. (7) 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 June 16, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-13407 Filed 6-28-17; 8:45 am] BILLING CODE 4910-13-P
![29363
Rules and Regulations Federal Register
Vol. 82, No. 124
Thursday, June 29, 2017
This section of the FEDERAL REGISTER of certain other publications listed in The NPRM published in the Federal
contains regulatory documents having general this AD as of December 29, 2015 (80 FR Register on February 15, 2017 (82 FR
applicability and legal effect, most of which 73099, November 24, 2015). 10721) (‘‘the NPRM’’). The NPRM was
are keyed to and codified in the Code of prompted by a determination that, for
ADDRESSES: For service information
Federal Regulations, which is published under certain airplanes, additional
50 titles pursuant to 44 U.S.C. 1510. identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1 modification instructions must be
The Code of Federal Regulations is sold by Rond Point Maurice Bellonte, 31707 accomplished to allow installation of
the Superintendent of Documents. Blagnac Cedex, France; telephone +33 5 the minimum FWC and FAC
61 93 36 96; fax +33 5 61 93 44 51; email configuration compatible with SRIW
account.airworth-eas@airbus.com; activation. The NPRM proposed to
DEPARTMENT OF TRANSPORTATION Internet http://www.airbus.com. You continue to require modification of the
may view this referenced service pin programming of the FWC to activate
Federal Aviation Administration the SRIW logic; and an inspection to
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue determine the part numbers of the FWC
14 CFR Part 39 and the FAC, and replacement of the
SW., Renton, WA. For information on
[Docket No. FAA–2016–9573; Directorate the availability of this material at the FWC and FAC if necessary. The NPRM
Identifier 2016–NM–149–AD; Amendment FAA, call 425–227–1221. It is also also proposed, for certain airplanes, to
39–18938; AD 2017–13–08] available on the Internet at http:// also require accomplishment of
RIN 2120–AA64 www.regulations.gov by searching for additional modification instructions to
and locating Docket No. FAA–2016– install the minimum FWC and FAC
Airworthiness Directives; Airbus 9573. configuration compatible with SRIW
Airplanes activation. We are issuing this AD to
Examining the AD Docket prevent detachment of the vertical tail
AGENCY: Federal Aviation You may examine the AD docket on plane and consequent loss of control of
Administration (FAA), Department of
the Internet at http:// the airplane.
Transportation (DOT).
www.regulations.gov by searching for The European Aviation Safety Agency
ACTION: Final rule. and locating Docket No. FAA–2016– (EASA), which is the Technical Agent
SUMMARY: We are superseding 9573; or in person at the Docket for the Member States of the European
Airworthiness Directive (AD) 2015–23– Management Facility between 9 a.m. Union, has issued EASA Airworthiness
13, for all Airbus Model A318 and A319 and 5 p.m., Monday through Friday, Directive 2016–0132, dated July 5, 2016;
series airplanes, Model A320–211, –212, except Federal holidays. The AD docket corrected July 20, 2016 (referred to after
–214, –231, –232, and –233 airplanes, contains this AD, the regulatory this as the Mandatory Continuing
and Model A321–111, –112, –131, –211, evaluation, any comments received, and Airworthiness Information, or ‘‘the
–212, –213, –231, and –232 airplanes. other information. The address for the MCAI’’), to correct an unsafe condition
AD 2015–23–13 required modification Docket Office (telephone 800–647–5527) for all Airbus Model A318 and A319
of the pin programming of the flight is Docket Management Facility, U.S. series airplanes, Model A320–211, –212,
warning computer (FWC) to activate the Department of Transportation, Docket –214, –231, –232, and –233 airplanes,
stop rudder input warning (SRIW) logic; Operations, M–30, West Building and Model A321–111, –112, –131, –211,
and an inspection to determine the part Ground Floor, Room W12–140, 1200 –212, –213, –231, and –232 airplanes.
numbers of the FWC and the flight New Jersey Avenue SE., Washington, The MCAI states:
augmentation computer (FAC), and DC 20590. During design reviews that were conducted
replacement of the FWC and FAC if FOR FURTHER INFORMATION CONTACT: following safety recommendations related to
necessary. This new AD, for certain Sanjay Ralhan, Aerospace Engineer, in-service incidents and one accident on
airplanes, also requires accomplishment International Branch, ANM–116, another aircraft type, it has been determined
of additional modification instructions Transport Airplane Directorate, FAA, that, in specific flight conditions, the
to install the minimum FWC and FAC 1601 Lind Avenue SW., Renton, WA allowable load limits on the vertical tail
configuration compatible with SRIW 98057–3356; telephone 425–227–1405; plane could be reached and possibly
exceeded.
activation. This AD was prompted by a fax 425–227–1149. This condition, if not corrected, could lead
determination that, in specific flight SUPPLEMENTARY INFORMATION: to in-flight detachment of the vertical tail
conditions, the allowable load limits on plane, possibly resulting in loss of control of
the vertical tail plane could be reached Discussion
the aeroplane.
and possibly exceeded. We are issuing We issued a notice of proposed To address this unsafe condition, Airbus
this AD to address the unsafe condition rulemaking (NPRM) to amend 14 CFR developed modifications within the flight
on these products. part 39 to supersede AD 2015–23–13, augmentation computer (FAC) to reduce the
DATES: This AD is effective August 3, Amendment 39–18330 (80 FR 73099, vertical tail plane stress and to activate a
November 24, 2015) (‘‘AD 2015–23– conditional aural warning within the flight
nlaroche on DSK30NT082PROD with RULES
2017. warning computer (FWC) to further protect
The Director of the Federal Register 13’’). AD 2015–23–13 applied to all
against pilot induced rudder doublets.
approved the incorporation by reference Airbus Model A318 and A319 series Consequently, EASA issued AD 2014–0217
of certain publications listed in this AD airplanes, Model A320–211, –212, –214, (later revised) [which corresponds to FAA
as of August 3, 2017. –231, –232, and –233 airplanes, and AD 2015–23–13] to require installation and
The Director of the Federal Register Model A321–111, –112, –131, –211, activation of the stop rudder input warning
approved the incorporation by reference –212, –213, –231, and –232 airplanes. (SRIW) logic. In addition, that [EASA] AD
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![29364 Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Rules and Regulations
required upgrades of the FAC and FWC, to failure of design, development, approved parts are already addressed in
introduce the SRIW logic and SRIW aural oversight and approval processes at the paragraph (l) of this AD. To clarify,
capability, respectively. After modification, EASA and the FAA. Mr. Barrance FWCs approved after March 5, 2015, are
the [EASA] AD prohibited (re)installation of
asserted that the FAA must do a an approved method of compliance with
certain Part Number (P/N) FWC and FAC.
Since EASA AD 2014–0217R1 was issued, comprehensive review of these the requirements of paragraph (h) or (j)
Airbus made available additional processes and evaluate the extent that of this AD, provided the requirements
modification instructions that, for certain the flying public has been exposed to specified in paragraphs (l)(1) and (l)(2)
aeroplanes, must be accomplished to allow risks due to delayed processes in of this AD are met. We have not
installation of the minimum FWC and FAC releasing this AD. changed this AD in this regard.
configuration compatible with SRIW We do not agree with Mr. Geoffrey
activation. Conclusion
Barrance’s comments. Mr. Barrance has
For the reasons described above, this We reviewed the available data,
[EASA] AD retains the requirements of EASA
submitted no data to substantiate his
claims. This rulemaking action simply including the comments received, and
AD 2014–0217R1, which is superseded, and
includes reference to modification supersedes a previous AD in order to determined that air safety and the
instructions, which must be accomplished on mandate accomplishment of additional public interest require adopting this AD
certain aeroplanes. modification instructions to ensure with the change described previously
This [EASA] AD is republished to remove design compatibility. Furthermore, we and minor editorial changes. We have
a typographical error in Appendix 1 [of the and our bilateral partner, EASA, work determined that these changes:
EASA AD]. closely with Airbus to ensure that • Are consistent with the intent that
You may examine the MCAI in the design solutions are certificated based was proposed in the NPRM for
AD docket on the Internet at http:// on applicable airworthiness regulations correcting the unsafe condition; and
www.regulations.gov by searching for prior to mandating those solutions to • Do not add any additional burden
and locating Docket No. FAA–2016– upon the public than was already
mitigate safety risks. We also ensure that
9573. proposed in the NPRM.
all appropriate instructions and parts
Comments are available at the appropriate time to Related Service Information Under 1
comply with AD requirements. As a CFR Part 51
We gave the public the opportunity to component of our safety management
participate in developing this AD. The Airbus has issued Service Bulletin
system, we continuously evaluate our A320–22–1480, Revision 02, dated
following presents the comments certification system and procedures and
received on the NPRM and the FAA’s March 30, 2015, and Service Bulletin
improve them when problems are A320–22–1480, Revision 03, dated
response to each comment. found. We have not revised this AD in October 13, 2015. This service
Request for Technical Details this regard. information describes procedures for
Mr. Geoffrey Barrance stated that the Request for Compliance Time Review modifying the pin programming to
public disclosure in the NPRM did not activate the SRIW logic. These
The Air Line Pilots Association, documents are distinct due to editorial
provide sufficient technical details and International (ALPA) stated that it
disclosure relative to the unsafe revisions.
agrees with the NPRM, but requested Airbus has also issued the following
condition; and that, presumably, the that we revisit the compliance
actions required by this proposed AD service information. The service
timeframe to ensure it is aligned with information describes procedures for
are to improve the protection provided the intent of the AD.
by the SRIW logic. Mr. Barrance noted replacing FWCs and FACs. These
The EASA has determined the documents are distinct since they apply
that the purpose of publication in the compliance times based on the overall
Federal Register is to provide public to different airplane configurations and
risk to the fleet, including the severity software packages.
disclosure. We infer the commenter is of the failure and the likelihood of the • Airbus Service Bulletin A320–22–
requesting that we provide additional failure’s occurrence. The FAA and 1375, dated January 15, 2014.
technical details. EASA worked with Airbus to ensure • Airbus Service Bulletin A320–22–
We do not agree with the commenter’s that all appropriate action(s) are taken at 1427, Revision 05, including Appendix
request. The technical details associated appropriate times to mitigate the risk to 01, dated November 24, 2014.
with correcting the unsafe condition the fleet. We have not changed this AD • Airbus Service Bulletin A320–22–
were already provided in the previously in this regard. 1447, Revision 03, dated April 21, 2015.
published AD, AD 2015–23–13. That • Airbus Service Bulletin A320–22–
AD and all service information that was Request for Correction of
Typographical Error 1454, dated February 12, 2014.
incorporated by reference in AD 2015– • Airbus Service Bulletin A320–22–
23–13 is posted on the public docket in Jetblue Airways (Jetblue) requested 1461, Revision 07, including Appendix
the Federal Docket Management System that we correct a typographical error in 01, dated March 23, 2015.
and is available on the Internet at http:// paragraph (i)(10) of the NPRM. Jetblue • Airbus Service Bulletin A320–22–
www.regulations.gov by searching for stated that it should be ‘‘FWC H2–F7,’’ 1502, dated November 14, 2014.
and locating Docket No. FAA–2015– not ‘‘FWC H–F7.’’ • Airbus Service Bulletin A320–22–
0251. This superseding AD only We agree with the commenter’s 1539, Revision 01, dated February 24,
mandates accomplishment of additional request and have revised this AD 2016.
modification instructions to ensure accordingly. • Airbus Service Bulletin A320–22–
design compatibility. We have not 1553, dated March 21, 2016.
Request for an Alternative Method of • Airbus Service Bulletin A320–22–
nlaroche on DSK30NT082PROD with RULES
revised this AD in this regard.
Compliance (AMOC) 1554, dated April 19, 2016.
Request for Review of Design Approval Jetblue requested that we include an • Airbus Service Bulletin A320–31–
Process and Compliance Time AMOC for FWC standard H2–F9D (P/N 1414, Revision 03, dated September 15,
Determination 350E053021818) in this AD. 2014.
Mr. Geoffrey Barrance asserted that We do not agree to include an AMOC This service information is reasonably
this rulemaking action is a result of in this AD because certain later available because the interested parties
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![Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Rules and Regulations 29365
have access to it through their normal 1. Is not a ‘‘significant regulatory exceeded. Exceeding allowable load limits
course of business or by the means action’’ under Executive Order 12866; could result in detachment of the vertical tail
identified in the ADDRESSES section. 2. Is not a ‘‘significant rule’’ under the plane. We are issuing this AD to prevent
DOT Regulatory Policies and Procedures detachment of the vertical tail plane and
Costs of Compliance (44 FR 11034, February 26, 1979); consequent loss of control of the airplane.
We estimate that this AD will affect 3. Will not affect intrastate aviation in (f) Compliance
1,032 airplanes of U.S. registry. Alaska; and Comply with this AD within the
The actions required by AD 2015–23– 4. Will not have a significant compliance times specified, unless already
13, and retained in this AD take about economic impact, positive or negative, done.
3 work-hours per product, at an average on a substantial number of small entities
under the criteria of the Regulatory (g) Retained Pin Programming Modification,
labor rate of $85 per work-hour. Based With New Service Information
on these figures, the estimated cost of Flexibility Act.
This paragraph restates the requirements of
the actions that are required by AD List of Subjects in 14 CFR Part 39 paragraph (g) of AD 2015–23–13, with new
2015–23–13 is $255 per product. service information. Within 48 months after
Air transportation, Aircraft, Aviation
We also estimate that it would take December 29, 2015 (the effective date of AD
safety, Incorporation by reference,
about 3 work-hours per product to 2015–23–13), modify the pin programming to
Safety. activate the stop rudder input warning
comply with the basic requirements of
this AD. The average labor rate is $85 Adoption of the Amendment (SRIW) logic, in accordance with the
per work-hour. Based on these figures, Accomplishment Instructions of Airbus
Accordingly, under the authority Service Bulletin A320–22–1480, Revision 02,
we estimate the cost of this AD on U.S. delegated to me by the Administrator, dated March 30, 2015; or Airbus Service
operators to be $263,160, or $255 per the FAA amends 14 CFR part 39 as Bulletin A320–22–1480, Revision 03, dated
product. follows: October 13, 2015. As of the effective date of
In addition, we estimate that any this AD, use only Airbus Service Bulletin
necessary follow-on actions will take PART 39—AIRWORTHINESS A320–22–1480, Revision 03, dated October
about 6 work-hours (3 work-hours for an DIRECTIVES 13, 2015.
FWC and 3 work-hours for an FAC), and (h) Retained Inspection To Determine Part
require parts costing $88,000 (FAC), for ■ 1. The authority citation for part 39
Numbers (P/Ns), Flight Warning Computer
a cost of $88,510 per product. We have continues to read as follows: (FWC) and Flight Augmentation Computer
no way of determining the number of Authority: 49 U.S.C. 106(g), 40113, 44701. (FAC) Replacement, With New Replacement
aircraft that might need these actions. Part Numbers
§ 39.13 [Amended]
Authority for This Rulemaking This paragraph restates the requirements of
■ 2. The FAA amends § 39.13 by paragraph (h) of AD 2015–23–13, with new
Title 49 of the United States Code removing Airworthiness Directive (AD) replacement part numbers. Prior to or
specifies the FAA’s authority to issue 2015–23–13, Amendment 39–18330 (80 concurrently with the actions required by
rules on aviation safety. Subtitle I, FR 73099, November 24, 2015), and paragraph (g) of this AD: Inspect the part
section 106, describes the authority of adding the following new AD: numbers of the FWC and the FAC installed
on the airplane. If any FWC or FAC having
the FAA Administrator. ‘‘Subtitle VII: 2017–13–08 Airbus: Amendment 39–18938; a part number identified in paragraph (h)(1)
Aviation Programs,’’ describes in more Docket No. FAA–2016–9573; Directorate or (h)(2) of this AD, as applicable, is installed
detail the scope of the Agency’s Identifier 2016–NM–149–AD. on an airplane, prior to or concurrently with
authority. (a) Effective Date the actions required by paragraph (g) of this
We are issuing this rulemaking under AD, replace all affected FWCs and FACs with
This AD is effective August 3, 2017. a unit having a part number identified in
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701: (b) Affected ADs figure 1 to paragraph (h)(3) of this AD, in
General requirements.’’ Under that accordance with the Accomplishment
This AD replaces AD 2015–23–13,
section, Congress charges the FAA with Instructions of the applicable Airbus service
Amendment 39–18330 (80 FR 73099,
information specified in paragraph (i) of this
promoting safe flight of civil aircraft in November 24, 2015) (‘‘AD 2015–23–13’’).
AD. As of the effective date of this AD, use
air commerce by prescribing regulations (c) Applicability only figure 1 to paragraph (h)(3) of this AD
for practices, methods, and procedures to identify the replacement part numbers.
This AD applies to the airplanes identified
the Administrator finds necessary for in paragraphs (c)(1) through (c)(4) of this AD, (1) Paragraphs (h)(1)(i) through (h)(1)(xvii)
safety in air commerce. This regulation certificated in any category, all manufacturer of this AD identify FWCs having part
is within the scope of that authority serial numbers. numbers that are non-compatible with the
because it addresses an unsafe condition (1) Airbus Model A318–111, –112, –121, SRIW activation required by paragraph (g) of
that is likely to exist or develop on and –122 airplanes. this AD.
products identified in this rulemaking (2) Airbus Model A319–111, –112, –113, (i) 350E017238484 (H1–D1).
–114, –115, –131, –132, and –133 airplanes. (ii) 350E053020303 (H2–E3).
action. (iii) 350E016187171 (C5).
(3) Airbus Model A320–211, –212, –214,
Regulatory Findings –231, –232, and –233 airplanes. (iv) 350E053020404 (H2–E4).
(4) Airbus Model A321–111, –112, –131, (v) 350E017248685 (H1–D2).
We determined that this AD will not –211, –212, –213, –231, and –232 airplanes. (vi) 350E053020606 (H2–F2).
have federalism implications under (vii) 350E017251414 (H1–E1).
Executive Order 13132. This AD will (d) Subject (viii) 350E053020707 (H2–F3).
not have a substantial direct effect on Air Transport Association (ATA) of (ix) 350E017271616 (H1–E2).
the States, on the relationship between America Code 22, Auto Flight; 31, (x) 350E053021010 (H2–F3P).
nlaroche on DSK30NT082PROD with RULES
the national government and the States, Instruments. (xi) 350E018291818 (H1–E3CJ).
(xii) 350E053020808 (H2–F4).
or on the distribution of power and (e) Reason (xiii) 350E018301919 (H1–E3P).
responsibilities among the various This AD was prompted by a determination (xiv) 350E053020909 (H2–F5).
levels of government. that, in specific flight conditions, the (xv) 350E018312020 (H1–E3Q).
For the reasons discussed above, I allowable load limits on the vertical tail (xvi) 350E053021111 (H2–F6).
certify that this AD: plane could be reached and possibly (xvii) 350E053020202 (H2–E2).
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![29368 Federal Register / Vol. 82, No. 124 / Thursday, June 29, 2017 / Rules and Regulations
maintenance or inspection program without 1601 Lind Avenue SW., Renton, WA. For 1601 Lind Avenue SW., Renton, WA.
obtaining approval of an AMOC, provided information on the availability of this For information on the availability of
the procedures and tests identified as RC can material at the FAA, call 425–227–1221. this material at the FAA, call 425–227–
be done and the airplane can be put back in (7) You may view this service information
an airworthy condition. Any substitutions or
1221. It is also available on the Internet
that is incorporated by reference at the
changes to procedures or tests identified as National Archives and Records at http://www.regulations.gov by
RC require approval of an AMOC. Administration (NARA). For information on searching for and locating Docket No.
the availability of this material at NARA, call FAA–2016–9437.
(o) Related Information
202–741–6030, or go to: http://
(1) Refer to Mandatory Continuing Examining the AD Docket
www.archives.gov/federal-register/cfr/ibr-
Airworthiness Information (MCAI) EASA locations.html. You may examine the AD docket on
Airworthiness Directive 2016–0132, dated the Internet at http://
July 5, 2016; corrected July 20, 2016; for Issued in Renton, Washington, on June 16,
related information. This MCAI may be 2017. www.regulations.gov by searching for
found in the AD docket on the Internet at Michael Kaszycki, and locating Docket No. FAA–2016–
http://www.regulations.gov by searching for Acting Manager, Transport Airplane 9437; or in person at the Docket
and locating Docket No. FAA–2016–9573. Directorate, Aircraft Certification Service. Management Facility between 9 a.m.
(2) For more information about this AD, and 5 p.m., Monday through Friday,
[FR Doc. 2017–13407 Filed 6–28–17; 8:45 am]
contact Sanjay Ralhan, Aerospace Engineer, except Federal holidays. The AD docket
International Branch, ANM–116, Transport BILLING CODE 4910–13–P
contains this AD, the regulatory
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
evaluation, any comments received, and
telephone 425–227–1405; fax 425–227–1149. DEPARTMENT OF TRANSPORTATION other information. The address for the
(3) Service information identified in this Docket Office (phone: 800–647–5527) is
AD that is not incorporated by reference is Federal Aviation Administration Docket Management Facility, U.S.
available at the addresses specified in Department of Transportation, Docket
paragraphs (p)(5) and (p)(6) of this AD. 14 CFR Part 39 Operations, M–30, West Building
(p) Material Incorporated by Reference Ground Floor, Room W12–140, 1200
[Docket No. FAA–2016–9437; Directorate
New Jersey Avenue SE., Washington,
(1) The Director of the Federal Register Identifier 2016–NM–131–AD; Amendment
approved the incorporation by reference 39–18941; AD 2017–13–11] DC 20590.
(IBR) of the service information listed in this FOR FURTHER INFORMATION CONTACT:
paragraph under 5 U.S.C. 552(a) and 1 CFR RIN 2120–AA64 Gideon Jose, Aerospace Engineer,
part 51. Systems and Equipment Branch, ACE–
(2) You must use this service information Airworthiness Directives; Gulfstream
Aerospace Corporation Airplanes 119A, FAA, Atlanta Aircraft
as applicable to do the actions required by Certification Office (ACO), 1701
this AD, unless this AD specifies otherwise.
(3) The following service information was
AGENCY: Federal Aviation Columbia Avenue, College Park, GA
approved for IBR on August 3, 2017. Administration (FAA), DOT. 30337; phone: 404–474–5569; fax: 404–
(i) Airbus Service Bulletin A320–22–1480, ACTION: Final rule. 474–5606; email: gideon.jose@faa.gov.
Revision 03, dated October 13, 2015. SUPPLEMENTARY INFORMATION:
(ii) Airbus Service Bulletin A320–22–1539, SUMMARY: We are adopting a new
Revision 01, dated February 24, 2016. airworthiness directive (AD) for all Discussion
(iii) Airbus Service Bulletin A320–22– Model G–IV airplanes. This AD was We issued a notice of proposed
1553, dated March 21, 2016. prompted by a report indicating that the
(iv) Airbus Service Bulletin A320–22– rulemaking (NPRM) to amend 14 CFR
G–IV gust lock system allows more part 39 by adding an AD that would
1554, dated April 19, 2016.
throttle travel than was intended and apply to all Gulfstream Aerospace
(4) The following service information was
approved for IBR on December 29, 2015 (80 could allow the throttle to be advanced Corporation Model G–IV airplanes. The
FR 73099, November 24, 2015). to reach take-off thrust. This AD NPRM published in the Federal
(i) Airbus Service Bulletin A320–22–1375, requires modification of the gust lock Register on December 12, 2016 (81 FR
dated January 15, 2014. system, and a revision of the 89397) (‘‘the NPRM’’). The NPRM was
(ii) Airbus Service Bulletin A320–22–1427, maintenance or inspection program to prompted by a report indicating that the
Revision 05, including Appendix 01, dated incorporate functional tests. We are
November 24, 2014.
G–IV gust lock system allows more
issuing this AD to address the unsafe throttle travel than was intended and
(iii) Airbus Service Bulletin A320–22–
condition on these products. could allow the throttle to be advanced
1447, Revision 03, dated April 21, 2015.
(iv) Airbus Service Bulletin A320–22– DATES: This AD is effective August 3, to reach take-off thrust. The intended
1454, dated February 12, 2014. 2017. function of the gust lock system is to
(v) Airbus Service Bulletin A320–22–1461, The Director of the Federal Register restrict throttle lever movement to a
Revision 07, including Appendix 01, dated approved the incorporation by reference maximum of 6 degrees of forward travel,
March 23, 2015. of certain publications listed in this AD which provides an unmistakable
(vi) Airbus Service Bulletin A320–22– as of August 3, 2017.
1480, Revision 02, dated March 30, 2015.
warning to the pilot that the gust lock
(vii) Airbus Service Bulletin A320–22– ADDRESSES: For service information system is still engaged, prohibiting the
1502, dated November 14, 2014. identified in this final rule, contact use of the primary flight control
(viii) Airbus Service Bulletin A320–31– Gulfstream Aerospace Corporation, surfaces. The NPRM proposed to require
1414, Revision 03, dated September 15, 2014. Technical Publications Dept., P.O. Box modification of the gust lock system,
(5) For service information identified in 2206, Savannah, GA 31402–2206; and a revision of the maintenance or
this AD, contact Airbus, Airworthiness telephone 800–810–4853; fax 912–965– inspection program to incorporate
nlaroche on DSK30NT082PROD with RULES
Office—EIAS, 1 Rond Point Maurice 3520; email pubs@gulfstream.com; functional tests. We are issuing this AD
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
Internet http://www.gulfstream.com/ to prevent the throttle lever movement
93 44 51; email account.airworth-eas@ product_support/technical_pubs/pubs/ from advancing more than 6 degrees of
airbus.com; Internet http://www.airbus.com. index.htm. You may view this forward travel, which could result in the
(6) You may view this service information referenced service information at the aircraft reaching near take-off thrust and
at the FAA, Transport Airplane Directorate, FAA, Transport Airplane Directorate, high velocities without primary flight
VerDate Sep<11>2014 15:31 Jun 28, 2017 Jkt 241001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\29JNR1.SGM 29JNR1](https://thefederalregister.org/doc/82_FR_29487/page/6.svg)
Document Created: 2018-11-14 10:17:15
Document Modified: 2018-11-14 10:17:15
| 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 August 3, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 82 FR 29363 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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