82 FR 10721 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 30 (February 15, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 30 (February 15, 2017)
| Page Range | 10721-10725 | |
| FR Document | 2017-02662 |
[Federal Register Volume 82, Number 30 (Wednesday, February 15, 2017)] [Proposed Rules] [Pages 10721-10725] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-02662] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 82, No. 30 / Wednesday, February 15, 2017 / Proposed Rules [[Page 10721]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9573; Directorate Identifier 2016-NM-149-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-23- 13, for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2015-23-13 currently requires 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. Since we issued AD 2015-23-13, we have determined that, for certain airplanes, additional modification instructions must be accomplished to allow installation of the minimum FWC and FAC configuration compatible with SRIW activation. This proposed AD would, for certain airplanes, also require accomplishment of additional modification instructions to install the minimum FWC and FAC configuration compatible with SRIW activation. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by April 3, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9573; Directorate Identifier 2016-NM-149-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On November 9, 2015, we issued AD 2015-23-13, Amendment 39-18330 (80 FR 73099, November 24, 2015) (``AD 2015-23-13''), for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2015-23-13 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. AD 2015-23-13 requires modification of the pin programming of the FWC to activate the SRIW logic; an inspection to determine the part numbers of the FWC and the FAC, and replacement of the FWC and FAC if necessary. We issued AD 2015-23-13 to prevent detachment of the vertical tail plane and consequent loss of control of the airplane. Since we issued AD 2015-23-13, we have determined 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 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, A319, A320, and A321 series 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 [[Page 10722]] 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 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. Related Service Information Under 1 CFR Part 51 Airbus has issued 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. 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 have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 1,032 airplanes of U.S. registry. The actions required by AD 2015-23-13, and retained in this proposed 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 proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2015-23-13, Amendment 39-18330 (80 FR 73099, November 24, 2015), and adding the following new AD: [[Page 10723]] Airbus: Docket No. FAA-2016-9573; Directorate Identifier 2016-NM- 149-AD. (a) Comments Due Date We must receive comments by April 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). (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 [[Page 10724]] [GRAPHIC] [TIFF OMITTED] TP15FE17.001 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 H-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 [[Page 10725]] 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 provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-22- 1480, Revision 02, dated March 30, 2015. (3) 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)(3)(i) through (m)(3)(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. (4) 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 ATTN: 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. Information may be emailed to: [email protected]. (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 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 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 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 [email protected]; Internet http://www.airbus.com. 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. Issued in Renton, Washington, on January 27, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-02662 Filed 2-14-17; 8:45 am] BILLING CODE 4910-13-P
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Proposed Rules Federal Register
Vol. 82, No. 30
Wednesday, February 15, 2017
This section of the FEDERAL REGISTER • Mail: U.S. Department of comments on the overall regulatory,
contains notices to the public of the proposed Transportation, Docket Operations, M– economic, environmental, and energy
issuance of rules and regulations. The 30, West Building Ground Floor, Room aspects of this proposed AD. We will
purpose of these notices is to give interested W12–140, 1200 New Jersey Avenue SE., consider all comments received by the
persons an opportunity to participate in the Washington, DC 20590. closing date and may amend this
rule making prior to the adoption of the final
rules.
• Hand Delivery: U.S. Department of proposed AD based on those comments.
Transportation, Docket Operations, M– We will post all comments we
30, West Building Ground Floor, Room receive, without change, to http://
DEPARTMENT OF TRANSPORTATION W12–140, 1200 New Jersey Avenue SE., www.regulations.gov, including any
Washington, DC, between 9 a.m. and 5 personal information you provide. We
Federal Aviation Administration p.m., Monday through Friday, except will also post a report summarizing each
Federal holidays. substantive verbal contact we receive
14 CFR Part 39 For service information identified in about this proposed AD.
this NPRM, contact Airbus,
[Docket No. FAA–2016–9573; Directorate Discussion
Identifier 2016–NM–149–AD]
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac On November 9, 2015, we issued AD
RIN 2120–AA64 Cedex, France; telephone +33 5 61 93 36 2015–23–13, Amendment 39–18330 (80
96; fax +33 5 61 93 44 51; email FR 73099, November 24, 2015) (‘‘AD
Airworthiness Directives; Airbus account.airworth-eas@airbus.com; 2015–23–13’’), for all Airbus Model
Airplanes Internet http://www.airbus.com. You A318, A319, A320, and A321 series
AGENCY: Federal Aviation may view this referenced service airplanes. AD 2015–23–13 was
Administration (FAA), DOT. information at the FAA, Transport prompted by a determination that, in
ACTION: Notice of proposed rulemaking Airplane Directorate, 1601 Lind Avenue specific flight conditions, the allowable
(NPRM). SW., Renton, WA. For information on load limits on the vertical tail plane
the availability of this material at the could be reached and possibly
SUMMARY: We propose to supersede FAA, call 425–227–1221. exceeded. Exceeding allowable load
Airworthiness Directive (AD) 2015–23– limits could result in detachment of the
Examining the AD Docket
13, for all Airbus Model A318, A319, vertical tail plane. AD 2015–23–13
A320, and A321 series airplanes. AD You may examine the AD docket on requires modification of the pin
2015–23–13 currently requires the Internet at http:// programming of the FWC to activate the
modification of the pin programming of www.regulations.gov by searching for SRIW logic; an inspection to determine
the flight warning computer (FWC) to and locating Docket No. FAA–2016– the part numbers of the FWC and the
activate the stop rudder input warning 9573; or in person at the Docket FAC, and replacement of the FWC and
(SRIW) logic; and an inspection to Management Facility between 9 a.m. FAC if necessary. We issued AD 2015–
determine the part numbers of the FWC and 5 p.m., Monday through Friday, 23–13 to prevent detachment of the
and the flight augmentation computer except Federal holidays. The AD docket vertical tail plane and consequent loss
(FAC), and replacement of the FWC and contains this proposed AD, the of control of the airplane.
FAC if necessary. Since we issued AD regulatory evaluation, any comments Since we issued AD 2015–23–13, we
2015–23–13, we have determined that, received, and other information. The have determined that, for certain
for certain airplanes, additional street address for the Docket Operations airplanes, additional modification
modification instructions must be office (telephone 800–647–5527) is in instructions must be accomplished to
accomplished to allow installation of the ADDRESSES section. Comments will allow installation of the minimum FWC
the minimum FWC and FAC be available in the AD docket shortly and FAC configuration compatible with
configuration compatible with SRIW after receipt. SRIW activation.
activation. This proposed AD would, for FOR FURTHER INFORMATION CONTACT: The European Aviation Safety Agency
certain airplanes, also require Sanjay Ralhan, Aerospace Engineer, (EASA), which is the Technical Agent
accomplishment of additional International Branch, ANM–116, for the Member States of the European
modification instructions to install the Transport Airplane Directorate, FAA, Union, has issued EASA Airworthiness
minimum FWC and FAC configuration 1601 Lind Avenue SW., Renton, WA Directive 2016–0132, dated July 5, 2016;
compatible with SRIW activation. We 98057–3356; telephone 425–227–1405; corrected July 20, 2016 (referred to after
are proposing this AD to address the fax 425–227–1149. this as the Mandatory Continuing
unsafe condition on these products. SUPPLEMENTARY INFORMATION: Airworthiness Information, or ‘‘the
DATES: We must receive comments on MCAI’’), to correct an unsafe condition
this proposed AD by April 3, 2017. Comments Invited
for all Airbus Model A318, A319, A320,
mstockstill on DSK3G9T082PROD with PROPOSALS
ADDRESSES: You may send comments, We invite you to send any written and A321 series airplanes. The MCAI
using the procedures found in 14 CFR relevant data, views, or arguments about states:
11.43 and 11.45, by any of the following this proposed AD. Send your comments
During design reviews that were conducted
methods: to an address listed under the following safety recommendations related to
• Federal eRulemaking Portal: Go to ADDRESSES section. Include ‘‘Docket No. in-service incidents and one accident on
http://www.regulations.gov. Follow the FAA–2016–9573; Directorate Identifier another aircraft type, it has been determined
instructions for submitting comments. 2016–NM–149–AD’’ at the beginning of that, in specific flight conditions, the
• Fax: 202–493–2251. your comments. We specifically invite allowable load limits on the vertical tail
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![10722 Federal Register / Vol. 82, No. 30 / Wednesday, February 15, 2017 / Proposed Rules
plane could be reached and possibly • Airbus Service Bulletin A320–22– Aviation Programs,’’ describes in more
exceeded. 1502, dated November 14, 2014. detail the scope of the Agency’s
This condition, if not corrected, could lead • Airbus Service Bulletin A320–22– authority.
to in-flight detachment of the vertical tail 1539, Revision 01, dated February 24, We are issuing this rulemaking under
plane, possibly resulting in loss of control of
2016. the authority described in ‘‘Subtitle VII,
the aeroplane.
To address this unsafe condition, Airbus
• Airbus Service Bulletin A320–22– Part A, Subpart III, Section 44701:
developed modifications within the flight 1553, dated March 21, 2016. General requirements.’’ Under that
augmentation computer (FAC) to reduce the • Airbus Service Bulletin A320–22– section, Congress charges the FAA with
vertical tail plane stress and to activate a 1554, dated April 19, 2016. promoting safe flight of civil aircraft in
conditional aural warning within the flight • Airbus Service Bulletin A320–31– air commerce by prescribing regulations
warning computer (FWC) to further protect 1414, Revision 03, dated September 15, for practices, methods, and procedures
against pilot induced rudder doublets. 2014. the Administrator finds necessary for
Consequently, EASA issued AD 2014–0217 This service information is reasonably safety in air commerce. This regulation
(later revised) [which corresponds to FAA available because the interested parties
AD 2015–23–13] to require installation and
is within the scope of that authority
have access to it through their normal because it addresses an unsafe condition
activation of the stop rudder input warning
course of business or by the means that is likely to exist or develop on
(SRIW) logic. In addition, that [EASA] AD
required upgrades of the FAC and FWC, to identified in the ADDRESSES section. products identified in this rulemaking
introduce the SRIW logic and SRIW aural FAA’s Determination and Requirements action.
capability, respectively. After modification, of This Proposed AD
the [EASA] AD prohibited (re)installation of Regulatory Findings
certain Part Number (P/N) FWC and FAC. This product has been approved by We determined that this proposed AD
Since EASA AD 2014–0217R1 was issued, the aviation authority of another would not have federalism implications
Airbus made available additional country, and is approved for operation under Executive Order 13132. This
modification instructions that, for certain in the United States. Pursuant to our
aeroplanes, must be accomplished to allow
proposed AD would not have a
bilateral agreement with the State of substantial direct effect on the States, on
installation of the minimum FWC and FAC Design Authority, we have been notified
configuration compatible with SRIW the relationship between the national
activation.
of the unsafe condition described in the Government and the States, or on the
For the reasons described above, this MCAI and service information distribution of power and
[EASA] AD retains the requirements of EASA referenced above. We are proposing this responsibilities among the various
AD 2014–0217R1, which is superseded, and AD because we evaluated all pertinent levels of government.
includes reference to modification information and determined an unsafe For the reasons discussed above, I
instructions, which must be accomplished on condition exists and is likely to exist or certify this proposed regulation:
certain aeroplanes. develop on other products of these same 1. Is not a ‘‘significant regulatory
This [EASA] AD is republished to remove type designs.
a typographical error in Appendix 1 [of the action’’ under Executive Order 12866;
EASA AD]. Costs of Compliance 2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
You may examine the MCAI in the We estimate that this proposed AD (44 FR 11034, February 26, 1979);
AD docket on the Internet at http:// affects 1,032 airplanes of U.S. registry. 3. Will not affect intrastate aviation in
www.regulations.gov by searching for The actions required by AD 2015–23– Alaska; and
and locating Docket No. FAA–2016– 13, and retained in this proposed AD 4. Will not have a significant
9573. take about 3 work-hours per product, at economic impact, positive or negative,
an average labor rate of $85 per work- on a substantial number of small entities
Related Service Information Under 1 hour. Based on these figures, the
CFR Part 51 under the criteria of the Regulatory
estimated cost of the actions that are Flexibility Act.
Airbus has issued Service Bulletin required by AD 2015–23–13 is $255 per
A320–22–1480, Revision 03, dated product. List of Subjects in 14 CFR Part 39
October 13, 2015. This service We also estimate that it would take Air transportation, Aircraft, Aviation
information describes procedures for about 3 work-hours per product to safety, Incorporation by reference,
modifying the pin programming to comply with the basic requirements of Safety.
activate the SRIW logic. this proposed AD. The average labor
Airbus has also issued the following rate is $85 per work-hour. Based on The Proposed Amendment
service information. The service these figures, we estimate the cost of Accordingly, under the authority
information describes procedures for this proposed AD on U.S. operators to delegated to me by the Administrator,
replacing FWCs and FACs. These be $263,160, or $255 per product. the FAA proposes to amend 14 CFR part
documents are distinct since they apply In addition, we estimate that any 39 as follows:
to different airplane configurations and necessary follow-on actions will take
software packages. about 6 work-hours (3 work-hours for an PART 39—AIRWORTHINESS
• Airbus Service Bulletin A320–22– FWC and 3 work-hours for an FAC), and DIRECTIVES
1375, dated January 15, 2014. require parts costing $88,000 (FAC), for
• Airbus Service Bulletin A320–22– a cost of $88,510 per product. We have ■ 1. The authority citation for part 39
1427, Revision 05, including Appendix no way of determining the number of continues to read as follows:
mstockstill on DSK3G9T082PROD with PROPOSALS
01, dated November 24, 2014. aircraft that might need these actions. Authority: 49 U.S.C. 106(g), 40113, 44701.
• Airbus Service Bulletin A320–22–
1447, Revision 03, dated April 21, 2015. Authority for This Rulemaking § 39.13 [Amended]
• Airbus Service Bulletin A320–22– Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
1454, dated February 12, 2014. specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
• Airbus Service Bulletin A320–22– rules on aviation safety. Subtitle I, 2015–23–13, Amendment 39–18330 (80
1461, Revision 07, including Appendix section 106, describes the authority of FR 73099, November 24, 2015), and
01, dated March 23, 2015. the FAA Administrator. ‘‘Subtitle VII: adding the following new AD:
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![Federal Register / Vol. 82, No. 30 / Wednesday, February 15, 2017 / Proposed Rules 10725
in lieu of this inspection if the part numbers Bulletin A320–22–1480, Revision 02, dated or lacking a principal inspector, the manager
of the FWC and FAC can be conclusively March 30, 2015. of the local flight standards district office/
determined from that review. If any FWC or (3) This paragraph restates the credit certificate holding district office.
FAC having a part number identified in provided by paragraph (m)(2) of AD 2015– (ii) AMOCs approved previously for 2015–
paragraph (h)(1) or (h)(2) of this AD, as 23–13. This paragraph provides credit for 23–13, are approved as AMOCs for the
applicable, is installed on a post Airbus actions required by paragraph (i) of this AD,
corresponding provisions of this AD.
Modification 154473 airplane: Within 30 if those actions were performed before
December 29, 2015 (the effective date of AD (2) Contacting the Manufacturer: As of the
days after December 29, 2015, do the
2015–23–13) using the applicable Airbus effective date of this AD, for any requirement
replacement required by paragraph (h) of this
AD. service information identified in paragraphs in this AD to obtain corrective actions from
(m)(3)(i) through (m)(3)(xviii) of this AD. a manufacturer, the action must be
(k) Retained Parts Installation Prohibitions, (i) Airbus Service Bulletin A320–22–1427, accomplished using a method approved by
With New Requirements dated January 25, 2013. the Manager, International Branch, ANM–
This paragraph restates the parts (ii) Airbus Service Bulletin A320–22–1427, 116, Transport Airplane Directorate, FAA; or
installation prohibitions specified in Revision 01, dated July 30, 2013. the EASA; or Airbus’s EASA DOA. If
paragraph (k) of AD 2015–23–13, with new (iii) Airbus Service Bulletin A320–22–
1427, Revision 02, dated October 14, 2013. approved by the DOA, the approval must
requirements. include the DOA-authorized signature.
(1) After modification of an airplane as (iv) Airbus Service Bulletin A320–22–
1427, Revision 03, dated November 8, 2013. (3) Required for Compliance (RC): If any
required by paragraphs (g), (h), or (j) of this
(v) Airbus Service Bulletin A320–22–1427, service information contains procedures or
AD: Do not install on that airplane any FWC
having a part number listed in paragraph Revision 04, dated February 11, 2014. tests that are identified as RC, those
(vi) Airbus Service Bulletin A320–22– procedures and tests must be done to comply
(h)(1) of this AD or any FAC having a part
1447, dated October 18, 2013. with this AD; any procedures or tests that are
number listed in paragraph (h)(2) of this AD.
(vii) Airbus Service Bulletin A320–22– not identified as RC are recommended. Those
(2) For an airplane that does not have a
1447, Revision 01, dated September 18, 2014.
FWC having a part number listed in procedures and tests that are not identified
(viii) Airbus Service Bulletin A320–22–
paragraph (h)(1) of this AD and does not have 1447, Revision 02, dated December 2, 2014. as RC may be deviated from using accepted
a FAC having a part number listed in (ix) Airbus Service Bulletin A320–22– methods in accordance with the operator’s
paragraph (h)(2) of this AD: As of the 1461, dated October 31, 2013. maintenance or inspection program without
effective date of this AD, do not install a (x) Airbus Service Bulletin A320–22–1461, obtaining approval of an AMOC, provided
FWC having a part number listed in Revision 01, dated February 25, 2014. the procedures and tests identified as RC can
paragraph (h)(1) of this AD or a FAC having (xi) Airbus Service Bulletin A320–22– be done and the airplane can be put back in
a part number listed in paragraph (h)(2) of 1461, Revision 02, dated April 30, 2014.
this AD. an airworthy condition. Any substitutions or
(xii) Airbus Service Bulletin A320–22– changes to procedures or tests identified as
(l) Retained Later Approved Parts, With a 1461, Revision 03, dated July 17, 2014. RC require approval of an AMOC.
Different Effective Date (xiii) Airbus Service Bulletin A320–22–
1461, Revision 04, dated September 15, 2014. (o) Related Information
This paragraph restates the requirements of (xiv) Airbus Service Bulletin A320–22–
paragraph (l) of AD 2015–23–13, with a (1) Refer to Mandatory Continuing
1461, Revision 05, dated November 13, 2014.
different effective date. Installation of a (xv) Airbus Service Bulletin A320–22– Airworthiness Information (MCAI) EASA
version (part number) of the FWC or FAC 1461, Revision 06, dated January 21, 2015. Airworthiness Directive 2016–0132, dated
approved after March 5, 2015 (the effective (xvi) Airbus Service Bulletin A320–31– July 5, 2016; corrected July 20, 2016; for
date of European Aviation Safety Agency 1414, dated December 19, 2012. related information. This MCAI may be
(EASA) AD 2014–0217R1), is an approved (xvii) Airbus Service Bulletin A320–31– found in the AD docket on the Internet at
method of compliance with the requirements 1414, Revision 01, dated March 21, 2013. http://www.regulations.gov by searching for
of paragraph (h) or (j) of this AD, provided (xviii) Airbus Service Bulletin A320–31– and locating Docket No. FAA–2016–9573.
the requirements specified in paragraphs 1414, Revision 02, dated July 30, 2013.
(l)(1) and (l)(2) of this AD are met. (2) For service information identified in
(4) This paragraph provides credit for this AD, contact Airbus, Airworthiness
(1) The version (part number) must be actions required by paragraph (i) of this AD,
approved by the Manager, International Office—EIAS, 1 Rond Point Maurice
if those actions were performed before the
Branch, ANM–116, Transport Airplane effective date of this AD using Airbus Service Bellonte, 31707 Blagnac Cedex, France;
Directorate, FAA; or EASA; or Airbus’s EASA Bulletin A320–22–1539, dated December 28, telephone +33 5 61 93 36 96; fax +33 5 61
Design Organization Approval (DOA). 2015. 93 44 51; email account.airworth-eas@
(2) The installation must be accomplished airbus.com; Internet http://www.airbus.com.
using a method approved by the Manager, (n) Other FAA AD Provisions
You may view this service information at the
International Branch, ANM–116, Transport The following provisions also apply to this FAA, Transport Airplane Directorate, 1601
Airplane Directorate, FAA; or EASA; or AD: Lind Avenue SW., Renton, WA. For
Airbus’s EASA DOA. (1) Alternative Methods of Compliance information on the availability of this
(AMOCs): The Manager, International
(m) Credit for Previous Actions material at the FAA, call 425–227–1221.
Branch, ANM–116, Transport Airplane
(1) This paragraph restates the credit Directorate, FAA, has the authority to Issued in Renton, Washington, on January
provided by paragraph (m)(1) of AD 2015– approve AMOCs for this AD, if requested 27, 2017.
23–13. This paragraph provides credit for using the procedures found in 14 CFR 39.19.
actions required by paragraph (g) of this AD, Dionne Palermo,
In accordance with 14 CFR 39.19, send your
if those actions were performed before request to your principal inspector or local Acting Manager, Transport Airplane
December 29, 2015 (the effective date of AD Flight Standards District Office, as Directorate, Aircraft Certification Service.
2015–23–13) using the service information appropriate. If sending information directly [FR Doc. 2017–02662 Filed 2–14–17; 8:45 am]
specified in paragraphs (m)(1)(i) or (m)(1)(ii) to the International Branch, send it to ATTN:
mstockstill on DSK3G9T082PROD with PROPOSALS
BILLING CODE 4910–13–P
of this AD. Sanjay Ralhan, Aerospace Engineer,
(i) Airbus Service Bulletin A320–22–1480, International Branch, ANM–116, Transport
dated July 9, 2014. Airplane Directorate, FAA, 1601 Lind
(ii) Airbus Service Bulletin A320–22–1480, Avenue SW., Renton, WA 98057–3356;
Revision 01, dated February 6, 2015. telephone 425–227–1405; fax 425–227–1149.
(2) This paragraph provides credit for Information may be emailed to: 9-ANM-116-
actions required by paragraph (g) of this AD, AMOC-REQUESTS@faa.gov.
if those actions were performed before the (i) Before using any approved AMOC,
effective date of this AD using Airbus Service notify your appropriate principal inspector,
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Document Created: 2017-02-15 00:54:57
Document Modified: 2017-02-15 00:54:57
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by April 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 10721 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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