80 FR 73099 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 226 (November 24, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 226 (November 24, 2015)
| Page Range | 73099-73103 | |
| FR Document | 2015-29702 |
[Federal Register Volume 80, Number 226 (Tuesday, November 24, 2015)] [Rules and Regulations] [Pages 73099-73103] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-29702] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0251; Directorate Identifier 2014-NM-200-AD; Amendment 39-18330; AD 2015-23-13] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. 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 could result in detachment of the vertical tail plane. This AD requires modification of the pin programming 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. We are issuing this AD to prevent detachment of the vertical tail plane and consequent loss of control of the airplane. DATES: This AD becomes effective December 29, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 29, 2015. ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0251; or in person at the 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. 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. 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-2015- 0251. 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 by adding an AD that would apply to all Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on March 5, 2015 (80 FR 11960). The NPRM 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 could result in detachment of the vertical tail plane. The NPRM proposed 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. 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 2014-0217R1, dated February 26, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition. 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, in the worst case, to detachment of the [[Page 73100]] vertical tail plane in flight and consequent loss of the aeroplane. To prevent such a possibility, Airbus has 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 (ad.easa.europa.eu/blob/ easa_ad_2014_0217.pdf/AD_2014-0217_1) to require installation and activation of the stop rudder input warning (SRIW) logic. In addition, that [EASA] AD required, prior to or concurrent with modification of an aeroplane with the activation of the SRIW, upgrades of the FAC and FWC, to introduce the SRIW logic and SRIW aural capability, respectively. After modification, the [EASA] AD prohibited installation of certain Part Number (P/N) FWC and FAC. Since that [EASA] AD was issued, an additional previously- published Airbus Service Bulletin (SB) was identified, and a new SB was published, for the concurrent requirement to replace the FAC with a unit having a P/N as listed in Table 3 of Appendix 1 of the AD. For the reasons described above, this [EASA] AD is revised to amend paragraph (2), adding references to additional Airbus SBs. In addition, this AD requires, prior to or concurrent with modification of an airplane with the activation of the SRIW, upgrades of the FAC and FWC to introduce the SRIW logic and SRIW aural capability, respectively. After modification, this AD prohibits installation of FWCs and FACs having certain part numbers. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0251-0003. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 11960, March 5, 2015) and the FAA's response to each comment. Request To Refer to Revised Service Information Airbus requested that we refer to revised service information. We agree with the Airbus request to refer to revised service information. No additional work is required by the revised service information. We have revised paragraph (g) of this AD to refer to Airbus Service Bulletin A320-22-1480, Revision 02, dated March 30, 2015. We have added new paragraph (m)(1) of this AD to provide credit for the 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, dated July 9, 2014; or Airbus Service Bulletin A320-22-1480, Revision 01, dated February 6, 2015. We have revised paragraph (i) of this AD to refer in part to the following service information.Airbus Service Bulletin A320-22-1427, Revision 05, including Appendix 01, dated November 24, 2014 (FAC 622 hard B). Airbus Service Bulletin A320-22-1447, Revision 03, dated April 21, 2015 (FAC CAA02 hard C). Airbus Service Bulletin A320-22-1454, dated February 12, 2014 (FAC CAA02). Airbus Service Bulletin A320-22-1461, Revision 07, including Appendix 01, dated March 23, 2015 (FAC B623 hard B). Airbus Service Bulletin A320-22-1502, dated November 14, 2014 (FAC CAA02). We have redesignated paragraph (m) of the proposed AD (80 FR 11960, March 5, 2015) as new paragraph (m)(2) of this AD to provide credit for the actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the following additional service information. Airbus Service Bulletin A320-22-1427, Revision 04, dated February 11, 2014. Airbus Service Bulletin A320-22-1447, Revision 01, dated September 18, 2014. Airbus Service Bulletin A320-22-1447, Revision 02, dated December 2, 2014. Airbus Service Bulletin A320-22-1461, Revision 04, dated September 15, 2014. Airbus Service Bulletin A320-22-1461, Revision 05, dated November 13, 2014. Airbus Service Bulletin A320-22-1461, Revision 06, dated January 21, 2015. Request To Clarify Approved Parts United Airlines (UAL) requested that we split paragraph (h)(3)(iv) of the proposed AD (80 FR 11960, March 5, 2015) into two paragraphs to clarify the approved parts. UAL stated that paragraphs (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of the proposed AD clearly denote three of the four possible standards of FAC, but paragraph (h)(3)(iv) of the proposed AD leads one to believe that a FAC CAA02 hard C is required regardless of the airplane configuration. We agree with UAL's request to clarify the FWCs and FACs having the part numbers that are compatible with SRIW activation required by paragraph (g) of this AD. We have revised paragraph (h)(3)(iv) of the AD to state that for all airplanes configured with an FAC standard CAA01, an FAC having soft P/N G2856AAA02 installed on hard P/N C13206AA00 (CAA02 hard C) are compatible with SRIW activation required by paragraph (g) of this AD. We have added new paragraph (h)(3)(v) of this AD to state that for all airplane configurations, an FWC having P/ N 350E053021212 (H2-F7) are compatible with SRIW activation required by paragraph (g) of this AD. Request for Additional Details and Clarification Regarding SRIW Changes The National Transportation Safety Board (NTSB) stated that there are differences between the Airbus Model A300/A310 series airplane SRIW system and the Airbus Model A320 series airplane SRIW system. The NTSB explained that the Model A300/A310 series airplane SRIW contains a red warning light on the glareshield, which lights when the SRIW is activated; however, the NPRM (80 FR 11960, March 5, 2015) did not mention the warning light as part of the Model A320 series airplane SRIW. The NTSB also stated that details associated with the modifications of the FAC and FWC are not stated in the NPRM (80 FR 11960, March 5, 2015). The NTSB stated that without details regarding the changes associated with the Model A320 series airplane SRIW it cannot fully assess the FAA response for the Model A320 series airplanes to NTSB safety recommendations A-04-56 (http://www.ntsb.gov/safety/safety-recs/recletters/A04_56_62.pdf) and A-04-57 (http://www.ntsb.gov/safety/safety-recs/recletters/A04_56_62.pdf). The NTSB also wanted the FAA to clarify whether the Model A320 series airplane SRIW has more comprehensive protections compared with the Model A300 series airplane SRIW. We agree with the NTSB that there are differences between the Airbus Model A300/A310 series airplane and Model A318/A319/A320/A321 series airplane SRIW systems, such as, the latter does not include a light on the glareshield in front of each pilot; instead it includes a red master caution warning in addition to the aural synthetic voice warning to prevent pilots from making any further reversals. In addition, the Model Airbus A318/A319/A320/A321 series airplane SRIW modification includes a rudder travel limiter unit (RTLU) modification in the FAC that minimizes the available deflections for all the possible combinations of altitude and speed. This will ensure that after one full rudder pedal reversal, the vertical tail [[Page 73101]] plane (VTP) loads remain within the safe limits. After reviewing the design, analyses, and simulator demonstrations, the FAA has concluded that these warnings will prevent the flightcrew from continuing the inappropriate rudder inputs prior to exceeding the ultimate design loads that could result in failure of the vertical tail plane. We have determined that details associated with our disposition to NTSB safety recommendations A-04-56 and A-04-57 are outside the context of this AD. We will provide those details directly to the NTSB in our response to the safety recommendations. We have not changed this final rule in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: Are consistent with the intent that was proposed in the NPRM (80 FR 11960, March 5, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 11960, March 5, 2015). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320-22-1480, Revision 02, dated March 30, 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. Airbus Service Bulletin A320-22-1375, dated January 15, 2014. Airbus Service Bulletin A320-22-1427, Revision 05, 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, dated March 23, 2015. Airbus Service Bulletin A320-22-1502, dated November 14, 2014. 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 of this AD. Costs of Compliance We estimate that this AD affects 953 airplanes of U.S. registry. We also estimate that it will 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 $243,015, 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), for a cost of up to $510 per product. We have received no definitive data that will enable us to provide part cost estimates for the on-condition actions specified in this AD. 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. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0251; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647- 5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2015-23-13 Airbus: Amendment 39-18330. Docket No. FAA-2015-0251; Directorate Identifier 2014-NM-200-AD. (a) Effective Date This AD becomes effective December 29, 2015. (b) Affected ADs None. (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. [[Page 73102]] (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 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) Pin Programming Modification Within 48 months after the effective date of this AD, 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. (h) Inspection To Determine Part Numbers (P/Ns), Flight Warning Computer (FWC) and Flight Augmentation Computer (FAC) Replacement 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 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. (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 (H1D1). (ii) 350E053020303 (H2E3). (iii) 350E016187171 (C5). (iv) 350E053020404 (H2E4). (v) 350E017248685 (H1D2). (vi) 350E053020606 (H2F2). (vii) 350E017251414 (H1E1). (viii) 350E053020707 (H2F3). (ix) 350E017271616 (H1E2). (x) 350E053021010 (H2F3P). (xi) 350E018291818 (H1E3CJ). (xii) 350E053020808 (H2F4). (xiii) 350E018301919 (H1E3P). (xiv) 350E053020909 (H2-F5). (xv) 350E018312020 (H1E3Q). (xvi) 350E053021111 (H2-F6). (xvii) 350E053020202 (H2E2). (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) Paragraphs (h)(3)(i) through (h)(3)(v) of this AD identify the FWCs and FACs having the part numbers that are compatible with SRIW activation required by paragraph (g) of this AD. (i) For airplane configurations with no sharklet, an FAC having P/N B397BAM0621 (621 hard B). (ii) For airplanes configured with sharklet A320 and A319, an FAC having P/N B397BAM0622 (622 hard B). (iii) For airplanes configured with sharklet A321, an FAC having P/N B397BAM0623 (623 hard B). (iv) For all airplanes configured with an FAC standard CAA01, an FAC having soft P/N G2856AAA02 installed on hard P/N C13206AA00 (CAA02 hard C). (v) For all airplane configurations, an FWC having P/N 350E053021212 (H2-F7). (i) Service Information for Actions Required by Paragraph (h) of This AD 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)(7) 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 A320-31-1414, Revision 03, dated September 15, 2014 (FWC H-F7). (j) Exclusion From Actions Required by Paragraphs (g) and (h) of This AD 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 the effective date of this AD, 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 the effective date of this AD, do the replacement required by paragraph (h) of this AD. (k) Parts Installation Prohibitions After modification of an airplane as required by paragraphs (g), (h), and (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. (l) Later Approved Parts Installation of a version (part number) of the FWC or FAC approved after the effective date of this AD 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 the European Aviation Safety Agency (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 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, dated July 9, 2014; or Airbus Service Bulletin A320-22-1480, Revision 01, dated February 6, 2015. This service information is not incorporated by reference in this AD. (2) 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 the applicable Airbus service information identified in paragraphs (m)(2)(i) through (m)(2)(xviii) of [[Page 73103]] this AD. This service information is not incorporated by reference in 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. (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: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) 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. (3) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0217R1, dated February 26, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0251-0003. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p(4) 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. (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. (3) 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. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on November 9, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-29702 Filed 11-23-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73099
International Branch, ANM–116, Transport the availability of this material at NARA, call Office—EIAS, 1 Rond Point Maurice
Airplane Directorate, FAA, 1601 Lind 202–741–6030, or go to: http://www.archives. Bellonte, 31707 Blagnac Cedex, France;
Avenue SW., Renton, WA 98057–3356; gov/federal-register/cfr/ibr-locations.html. telephone +33 5 61 93 36 96; fax +33 5
telephone 425–227–1137; fax 425–227–1149. Issued in Renton, Washington, on 61 93 44 51; email account.airworth-
Information may be emailed to: 9-ANM-116- November 12, 2015.
AMOC-REQUESTS@faa.gov. Before using
eas@airbus.com; Internet http://
any approved AMOC, notify your appropriate Michael Kaszycki, www.airbus.com. You may view this
principal inspector, or lacking a principal Acting Manager, Transport Airplane referenced service information at the
inspector, the manager of the local flight Directorate, Aircraft Certification Service. FAA, Transport Airplane Directorate,
standards district office/certificate holding [FR Doc. 2015–29682 Filed 11–23–15; 8:45 am] 1601 Lind Avenue SW., Renton, WA.
district office. The AMOC approval letter BILLING CODE 4910–13–P For information on the availability of
must specifically reference this AD. this material at the FAA, call 425–227–
(2) Contacting the Manufacturer: For any 1221. It is also available on the Internet
requirement in this AD to obtain corrective DEPARTMENT OF TRANSPORTATION at http://www.regulations.gov by
actions from a manufacturer, the action must
be accomplished using a method approved
searching for and locating Docket No.
Federal Aviation Administration FAA–2015–0251.
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or FOR FURTHER INFORMATION CONTACT:
14 CFR Part 39
the EASA; or ATR—GIE Avions de Transport Sanjay Ralhan, Aerospace Engineer,
Régional’s EASA DOA. If approved by the [Docket No. FAA–2015–0251; Directorate International Branch, ANM–116,
DOA, the approval must include the DOA- Identifier 2014–NM–200–AD; Amendment Transport Airplane Directorate, FAA,
authorized signature. 39–18330; AD 2015–23–13]
1601 Lind Avenue SW., Renton, WA
(n) Related Information RIN 2120–AA64 98057–3356; telephone 425–227–1405;
(1) Refer to Mandatory Continuing fax 425–227–1149.
Airworthiness Information (MCAI) EASA Airworthiness Directives; Airbus
Airplanes SUPPLEMENTARY INFORMATION:
Airworthiness Directive 2014–0074, dated
March 21, 2014, for related information. This
AGENCY: Federal Aviation Discussion
MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov/# Administration (FAA), Department of We issued a notice of proposed
!documentDetail;D=FAA-2015-0682-0002. Transportation (DOT). rulemaking (NPRM) to amend 14 CFR
(2) Service information identified in this ACTION: Final rule. part 39 by adding an AD that would
AD that is not incorporated by reference is apply to all Airbus Model A318, A319,
available at the addresses specified in SUMMARY: We are adopting a new A320, and A321 series airplanes. The
paragraphs (o)(3) and (o)(4) of this AD. airworthiness directive (AD) for all NPRM published in the Federal
Airbus Model A318, A319, A320, and Register on March 5, 2015 (80 FR
(o) Material Incorporated by Reference
A321 series airplanes. This AD was 11960). The NPRM was prompted by a
(1) The Director of the Federal Register prompted by a determination that, in
approved the incorporation by reference determination that, in specific flight
specific flight conditions, the allowable conditions, the allowable load limits on
(IBR) of the service information listed in this
load limits on the vertical tail plane
paragraph under 5 U.S.C. 552(a) and 1 CFR the vertical tail plane could be reached
part 51. could be reached and possibly
and possibly exceeded. Exceeding
(2) You must use this service information exceeded. Exceeding allowable load
allowable load could result in
as applicable to do the actions required by could result in detachment of the
detachment of the vertical tail plane.
this AD, unless this AD specifies otherwise. vertical tail plane. This AD requires
The NPRM proposed to require
(i) Messier-Bugatti-Dowty Service Bulletin modification of the pin programming
modification of the pin programming of
631–32–213, dated December 16, 2013. flight warning computer (FWC) to
(ii) Messier-Bugatti-Dowty Service Bulletin the FWC to activate the SRIW logic; and
activate the stop rudder input warning
631–32–214, dated January 13, 2014. an inspection to determine the part
(SRIW) logic; and an inspection to
(iii) Messier-Bugatti-Dowty Service numbers of the FWC and the FAC, and
determine the part numbers of the FWC
Bulletin 631–32–215, dated January 13, 2014.
and the flight augmentation computer replacement of the FWC and FAC if
(iv) Messier-Bugatti-Dowty Service Bulletin necessary. We are issuing this AD to
631–32–216, Revision 1, dated December 17, (FAC), and replacement of the FWC and
FAC if necessary. We are issuing this prevent detachment of the vertical tail
2013. Pages 4, 5, and 8 of this service bulletin plane and consequent loss of control of
are the original issue and are dated October AD to prevent detachment of the
vertical tail plane and consequent loss the airplane.
30, 2013.
(v) Messier-Bugatti-Dowty Service Bulletin of control of the airplane. The European Aviation Safety Agency
631–32–219, dated March 3, 2014. DATES: This AD becomes effective
(EASA), which is the Technical Agent
(vi) Messier-Bugatti-Dowty Service Bulletin December 29, 2015. for the Member States of the European
631–32–220, dated March 3, 2014. The Director of the Federal Register Union, has issued EASA Airworthiness
(3) For service information identified in Directive 2014–0217R1, dated February
this AD, contact ATR—GIE Avions de
approved the incorporation by reference
of certain publications listed in this AD 26, 2015 (referred to after this as the
Transport Régional, 1, Allée Pierre Nadot, Mandatory Continuing Airworthiness
31712 Blagnac Cedex, France; telephone +33 as of December 29, 2015.
Information, or ‘‘the MCAI’’), to correct
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; ADDRESSES: You may examine the AD
email continued.airworthiness@atr.fr;
an unsafe condition. The MCAI states:
docket on the Internet at http://www.
Internet http://www.aerochain.com. regulations.gov/#!docketDetail;D=FAA- During design reviews that were conducted
(4) You may view this service information 2015-0251; or in person at the Docket following safety recommendations related to
mstockstill on DSK4VPTVN1PROD with RULES
at the FAA, Transport Airplane Directorate, Management Facility, U.S. Department in-service incidents and one accident on
1601 Lind Avenue SW., Renton, WA. For another aircraft type, it has been determined
information on the availability of this
of Transportation, Docket Operations, that, in specific flight conditions, the
material at the FAA, call 425–227–1221. M–30, West Building Ground Floor, allowable load limits on the vertical tail
(5) You may view this service information Room W12–140, 1200 New Jersey plane could be reached and possibly
that is incorporated by reference at the Avenue SE., Washington, DC. exceeded.
National Archives and Records For service information identified in This condition, if not corrected, could lead,
Administration (NARA). For information on this AD, contact Airbus, Airworthiness in the worst case, to detachment of the
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![73100 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
vertical tail plane in flight and consequent dated July 9, 2014; or Airbus Service (g) of this AD. We have revised
loss of the aeroplane. Bulletin A320–22–1480, Revision 01, paragraph (h)(3)(iv) of the AD to state
To prevent such a possibility, Airbus has dated February 6, 2015. that for all airplanes configured with an
developed modifications within the flight
We have revised paragraph (i) of this FAC standard CAA01, an FAC having
augmentation computer (FAC) to reduce the
vertical tail plane stress and to activate a AD to refer in part to the following soft P/N G2856AAA02 installed on hard
conditional aural warning within the flight service information. P/N C13206AA00 (CAA02 hard C) are
warning computer (FWC) to further protect • Airbus Service Bulletin A320–22– compatible with SRIW activation
against pilot induced rudder doublets. 1427, Revision 05, including Appendix required by paragraph (g) of this AD. We
Consequently, EASA issued AD 2014–0217 01, dated November 24, 2014 (FAC 622 have added new paragraph (h)(3)(v) of
(ad.easa.europa.eu/blob/easa_ad_2014_ hard B). this AD to state that for all airplane
0217.pdf/AD_2014–0217_1) to require • Airbus Service Bulletin A320–22– configurations, an FWC having P/N
installation and activation of the stop rudder 1447, Revision 03, dated April 21, 2015 350E053021212 (H2–F7) are compatible
input warning (SRIW) logic. In addition, that
(FAC CAA02 hard C). with SRIW activation required by
[EASA] AD required, prior to or concurrent
with modification of an aeroplane with the
• Airbus Service Bulletin A320–22– paragraph (g) of this AD.
activation of the SRIW, upgrades of the FAC 1454, dated February 12, 2014 (FAC
CAA02). Request for Additional Details and
and FWC, to introduce the SRIW logic and Clarification Regarding SRIW Changes
SRIW aural capability, respectively. After • Airbus Service Bulletin A320–22–
modification, the [EASA] AD prohibited 1461, Revision 07, including Appendix The National Transportation Safety
installation of certain Part Number (P/N) 01, dated March 23, 2015 (FAC B623 Board (NTSB) stated that there are
FWC and FAC. hard B). differences between the Airbus Model
Since that [EASA] AD was issued, an • Airbus Service Bulletin A320–22– A300/A310 series airplane SRIW system
additional previously-published Airbus 1502, dated November 14, 2014 (FAC and the Airbus Model A320 series
Service Bulletin (SB) was identified, and a airplane SRIW system. The NTSB
new SB was published, for the concurrent
CAA02).
requirement to replace the FAC with a unit We have redesignated paragraph (m) explained that the Model A300/A310
having a P/N as listed in Table 3 of Appendix of the proposed AD (80 FR 11960, series airplane SRIW contains a red
1 of the AD. March 5, 2015) as new paragraph (m)(2) warning light on the glareshield, which
For the reasons described above, this of this AD to provide credit for the lights when the SRIW is activated;
[EASA] AD is revised to amend paragraph actions required by paragraph (i) of this however, the NPRM (80 FR 11960,
(2), adding references to additional Airbus AD, if those actions were performed March 5, 2015) did not mention the
SBs. before the effective date of this AD using warning light as part of the Model A320
In addition, this AD requires, prior to the following additional service series airplane SRIW. The NTSB also
or concurrent with modification of an information. stated that details associated with the
airplane with the activation of the • Airbus Service Bulletin A320–22– modifications of the FAC and FWC are
SRIW, upgrades of the FAC and FWC to 1427, Revision 04, dated February 11, not stated in the NPRM (80 FR 11960,
introduce the SRIW logic and SRIW 2014. March 5, 2015). The NTSB stated that
aural capability, respectively. After • Airbus Service Bulletin A320–22– without details regarding the changes
modification, this AD prohibits 1447, Revision 01, dated September 18, associated with the Model A320 series
installation of FWCs and FACs having 2014. airplane SRIW it cannot fully assess the
certain part numbers. You may examine • Airbus Service Bulletin A320–22– FAA response for the Model A320 series
the MCAI in the AD docket on the 1447, Revision 02, dated December 2, airplanes to NTSB safety
Internet at http://www.regulations.gov/# 2014. recommendations A–04–56 (http://
!documentDetail;D=FAA-2015-0251- • Airbus Service Bulletin A320–22– www.ntsb.gov/safety/safety-recs/
0003. 1461, Revision 04, dated September 15, recletters/A04_56_62.pdf) and A–04–57
2014. (http://www.ntsb.gov/safety/safety-recs/
Comments • Airbus Service Bulletin A320–22– recletters/A04_56_62.pdf). The NTSB
We gave the public the opportunity to 1461, Revision 05, dated November 13, also wanted the FAA to clarify whether
participate in developing this AD. The 2014. the Model A320 series airplane SRIW
following presents the comments • Airbus Service Bulletin A320–22– has more comprehensive protections
received on the NPRM (80 FR 11960, 1461, Revision 06, dated January 21, compared with the Model A300 series
March 5, 2015) and the FAA’s response 2015. airplane SRIW.
to each comment. We agree with the NTSB that there are
Request To Clarify Approved Parts differences between the Airbus Model
Request To Refer to Revised Service United Airlines (UAL) requested that A300/A310 series airplane and Model
Information we split paragraph (h)(3)(iv) of the A318/A319/A320/A321 series airplane
Airbus requested that we refer to proposed AD (80 FR 11960, March 5, SRIW systems, such as, the latter does
revised service information. 2015) into two paragraphs to clarify the not include a light on the glareshield in
We agree with the Airbus request to approved parts. UAL stated that front of each pilot; instead it includes a
refer to revised service information. No paragraphs (h)(3)(i), (h)(3)(ii), and red master caution warning in addition
additional work is required by the (h)(3)(iii) of the proposed AD clearly to the aural synthetic voice warning to
revised service information. We have denote three of the four possible prevent pilots from making any further
revised paragraph (g) of this AD to refer standards of FAC, but paragraph reversals. In addition, the Model Airbus
to Airbus Service Bulletin A320–22– (h)(3)(iv) of the proposed AD leads one A318/A319/A320/A321 series airplane
mstockstill on DSK4VPTVN1PROD with RULES
1480, Revision 02, dated March 30, to believe that a FAC CAA02 hard C is SRIW modification includes a rudder
2015. We have added new paragraph required regardless of the airplane travel limiter unit (RTLU) modification
(m)(1) of this AD to provide credit for configuration. in the FAC that minimizes the available
the actions required by paragraph (g) of We agree with UAL’s request to deflections for all the possible
this AD, if those actions were performed clarify the FWCs and FACs having the combinations of altitude and speed.
before the effective date of this AD using part numbers that are compatible with This will ensure that after one full
Airbus Service Bulletin A320–22–1480, SRIW activation required by paragraph rudder pedal reversal, the vertical tail
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![Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73101
plane (VTP) loads remain within the have access to it through their normal 2. Is not a ‘‘significant rule’’ under the
safe limits. After reviewing the design, course of business or by the means DOT Regulatory Policies and Procedures
analyses, and simulator demonstrations, identified in the ADDRESSES section of (44 FR 11034, February 26, 1979);
the FAA has concluded that these this AD. 3. Will not affect intrastate aviation in
warnings will prevent the flightcrew Alaska; and
from continuing the inappropriate Costs of Compliance 4. Will not have a significant
rudder inputs prior to exceeding the We estimate that this AD affects 953 economic impact, positive or negative,
ultimate design loads that could result airplanes of U.S. registry. on a substantial number of small entities
in failure of the vertical tail plane. We We also estimate that it will take under the criteria of the Regulatory
have determined that details associated about 3 work-hours per product to Flexibility Act.
with our disposition to NTSB safety comply with the basic requirements of Examining the AD Docket
recommendations A–04–56 and A–04– this AD. The average labor rate is $85
57 are outside the context of this AD. You may examine the AD docket on
per work-hour. Based on these figures, the Internet at http://www.regulations.
We will provide those details directly to we estimate the cost of this AD on U.S.
the NTSB in our response to the safety gov/#!docketDetail;D=FAA-2015-0251;
operators to be $243,015, or $255 per or in person at the Docket Management
recommendations. We have not changed product.
this final rule in this regard. Facility between 9 a.m. and 5 p.m.,
In addition, we estimate that any Monday through Friday, except Federal
Conclusion necessary follow-on actions will take holidays. The AD docket contains this
We reviewed the relevant data, about 6 work-hours (3 work-hours for an AD, the regulatory evaluation, any
considered the comments received, and FWC and 3 work-hours for an FAC), for comments received, and other
determined that air safety and the a cost of up to $510 per product. We information. The street address for the
public interest require adopting this AD have received no definitive data that Docket Operations office (telephone
with the changes described previously will enable us to provide part cost 800–647–5527) is in the ADDRESSES
and minor editorial changes. We have estimates for the on-condition actions section.
determined that these minor changes: specified in this AD. We have no way
• Are consistent with the intent that of determining the number of aircraft List of Subjects in 14 CFR Part 39
was proposed in the NPRM (80 FR that might need these actions. Air transportation, Aircraft, Aviation
11960, March 5, 2015) for correcting the safety, Incorporation by reference,
Authority for This Rulemaking
unsafe condition; and Safety.
• Do not add any additional burden Title 49 of the United States Code Adoption of the Amendment
upon the public than was already specifies the FAA’s authority to issue
proposed in the NPRM (80 FR 11960, rules on aviation safety. Subtitle I, Accordingly, under the authority
March 5, 2015). section 106, describes the authority of delegated to me by the Administrator,
We also determined that these the FAA Administrator. ‘‘Subtitle VII: the FAA amends 14 CFR part 39 as
changes will not increase the economic Aviation Programs,’’ describes in more follows:
burden on any operator or increase the detail the scope of the Agency’s
scope of this AD. PART 39—AIRWORTHINESS
authority.
DIRECTIVES
Related Service Information Under 1 We are issuing this rulemaking under
CFR Part 51 the authority described in ‘‘Subtitle VII, ■ 1. The authority citation for part 39
Airbus has issued Service Bulletin Part A, Subpart III, Section 44701: continues to read as follows:
A320–22–1480, Revision 02, dated General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701.
March 30, 2015. This service section, Congress charges the FAA with
promoting safe flight of civil aircraft in § 39.13 [Amended]
information describes procedures for
modifying the pin programming to air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by adding
activate the SRIW logic. for practices, methods, and procedures the following new airworthiness
Airbus has also issued the following the Administrator finds necessary for directive (AD):
service information. The service safety in air commerce. This regulation
2015–23–13 Airbus: Amendment 39–18330.
information describes procedures for is within the scope of that authority Docket No. FAA–2015–0251; Directorate
replacing FWCs and FACs. because it addresses an unsafe condition Identifier 2014–NM–200–AD.
• Airbus Service Bulletin A320–22– that is likely to exist or develop on
(a) Effective Date
1375, dated January 15, 2014. products identified in this rulemaking
• Airbus Service Bulletin A320–22– action. This AD becomes effective December 29,
1427, Revision 05, dated November 24, 2015.
2014. Regulatory Findings
(b) Affected ADs
• Airbus Service Bulletin A320–22– We determined that this AD will not None.
1447, Revision 03, dated April 21, 2015. have federalism implications under
• Airbus Service Bulletin A320–22– Executive Order 13132. This AD will
(c) Applicability
1454, dated February 12, 2014. not have a substantial direct effect on This AD applies to the airplanes identified
• Airbus Service Bulletin A320–22– the States, on the relationship between in paragraphs (c)(1) through (c)(4) of this AD,
1461, Revision 07, dated March 23, certificated in any category, all manufacturer
the national government and the States, serial numbers.
2015.
mstockstill on DSK4VPTVN1PROD with RULES
or on the distribution of power and (1) Airbus Model A318–111, –112, –121,
• Airbus Service Bulletin A320–22–
responsibilities among the various and –122 airplanes.
1502, dated November 14, 2014.
• Airbus Service Bulletin A320–31– levels of government. (2) Airbus Model A319–111, –112, –113,
For the reasons discussed above, I –114, –115, –131, –132, and –133 airplanes.
1414, Revision 03, dated September 15, (3) Airbus Model A320–211, –212, –214,
2014. certify that this AD: –231, –232, and –233 airplanes.
This service information is reasonably 1. Is not a ‘‘significant regulatory (4) Airbus Model A321–111, –112, –131,
available because the interested parties action’’ under Executive Order 12866; –211, –212, –213, –231, and –232 airplanes.
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![Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73103
this AD. This service information is not obtaining approval of an AMOC, provided Issued in Renton, Washington, on
incorporated by reference in this AD. the procedures and tests identified as RC can November 9, 2015.
(i) Airbus Service Bulletin A320–22–1427, be done and the airplane can be put back in Michael Kaszycki,
dated January 25, 2013. an airworthy condition. Any substitutions or Acting Manager, Transport Airplane
(ii) Airbus Service Bulletin A320–22–1427, changes to procedures or tests identified as Directorate, Aircraft Certification Service.
Revision 01, dated July 30, 2013. RC require approval of an AMOC.
(iii) Airbus Service Bulletin A320–22– [FR Doc. 2015–29702 Filed 11–23–15; 8:45 am]
(3) Contacting the Manufacturer: For any
1427, Revision 02, dated October 14, 2013. requirement in this AD to obtain corrective BILLING CODE 4910–13–P
(iv) Airbus Service Bulletin A320–22– actions from a manufacturer, the action must
1427, Revision 03, dated November 8, 2013. be accomplished using a method approved
(v) Airbus Service Bulletin A320–22–1427, by the Manager, International Branch, ANM– DEPARTMENT OF TRANSPORTATION
Revision 04, dated February 11, 2014. 116, Transport Airplane Directorate, FAA; or
(vi) Airbus Service Bulletin A320–22– the EASA; or Airbus’s EASA DOA. If Federal Aviation Administration
1447, dated October 18, 2013. approved by the DOA, the approval must
(vii) Airbus Service Bulletin A320–22– include the DOA-authorized signature. 14 CFR Part 71
1447, Revision 01, dated September 18, 2014.
(viii) Airbus Service Bulletin A320–22– (o) Related Information [Docket No. FAA–2015–1869; Airspace
1447, Revision 02, dated December 2, 2014. (1) Refer to Mandatory Continuing Docket No. 15–AGL–9]
(ix) Airbus Service Bulletin A320–22– Airworthiness Information (MCAI) EASA
1461, dated October 31, 2013. Airworthiness Directive 2014–0217R1, dated Establishment of Class E Airspace;
(x) Airbus Service Bulletin A320–22–1461, February 26, 2015, for related information. Newberry, MI
Revision 01, dated February 25, 2014. This MCAI may be found in the AD docket
(xi) Airbus Service Bulletin A320–22– on the Internet at http://www.regulations. AGENCY: Federal Aviation
1461, Revision 02, dated April 30, 2014. gov/#!documentDetail;D=FAA-2015-0251- Administration (FAA), DOT.
(xii) Airbus Service Bulletin A320–22– 0003. ACTION: Final rule; correction.
1461, Revision 03, dated July 17, 2014. (2) Service information identified in this
(xiii) Airbus Service Bulletin A320–22– AD that is not incorporated by reference is SUMMARY: This action corrects an error
1461, Revision 04, dated September 15, 2014. available at the addresses specified in in the legal description of a final rule
(xiv) Airbus Service Bulletin A320–22– paragraphs (p)(3) and (p(4) of this AD. published in the Federal Register of
1461, Revision 05, dated November 13, 2014. September 24, 2015, that establishes
(xv) Airbus Service Bulletin A320–22– (p) Material Incorporated by Reference
Class E airspace at the Newberry VHF
1461, Revision 06, dated January 21, 2015. (1) The Director of the Federal Register
Omni-Directional Range/Distance
(xvi) Airbus Service Bulletin A320–31– approved the incorporation by reference
(IBR) of the service information listed in this Measuring Equipment (VOR/DME),
1414, dated December 19, 2012.
(xvii) Airbus Service Bulletin A320–31– paragraph under 5 U.S.C. 552(a) and 1 CFR Newberry, MI. The legal description
1414, Revision 01, dated March 21, 2013. part 51. noted exclusionary language for Federal
(xviii) Airbus Service Bulletin A320–31– (2) You must use this service information airways and Canadian airspace not
1414, Revision 02, dated July 30, 2013. as applicable to do the actions required by required for this airspace.
this AD, unless this AD specifies otherwise. DATES: Effective date: 0901 UTC,
(n) Other FAA AD Provisions (i) Airbus Service Bulletin A320–22–1375, December 10, 2015. The Director of the
The following provisions also apply to this dated January 15, 2014.
Federal Register approves this
AD: (ii) Airbus Service Bulletin A320–22–1427,
(1) Alternative Methods of Compliance Revision 05, including Appendix 01, dated incorporation by reference action under
(AMOCs): The Manager, International November 24, 2014. 1 Code of Federal Regulations, Part 51,
Branch, ANM–116, Transport Airplane (iii) Airbus Service Bulletin A320–22– subject to the annual revision of FAA
Directorate, FAA, has the authority to 1447, Revision 03, dated April 21, 2015. Order 7400.9 and publication of
approve AMOCs for this AD, if requested (iv) Airbus Service Bulletin A320–22– conforming amendments.
using the procedures found in 14 CFR 39.19. 1454, dated February 12, 2014. FOR FURTHER INFORMATION CONTACT: Raul
In accordance with 14 CFR 39.19, send your (v) Airbus Service Bulletin A320–22–1461, Garza, Jr., Central Service Center,
request to your principal inspector or local Revision 07, including Appendix 01, dated
Flight Standards District Office, as March 23, 2015.
Operations Support Group, Federal
appropriate. If sending information directly (vi) Airbus Service Bulletin A320–22– Aviation Administration, Southwest
to the International Branch, send it to ATTN: 1480, Revision 02, dated March 30, 2015. Region, 10101 Hillwood Parkway., Fort
Sanjay Ralhan, Aerospace Engineer, (vii) Airbus Service Bulletin A320–22– Worth, TX 76177; telephone 817–222–
International Branch, ANM–116, Transport 1502, dated November 14, 2014. 5874.
Airplane Directorate, FAA, 1601 Lind (viii) Airbus Service Bulletin A320–31– SUPPLEMENTARY INFORMATION:
Avenue SW., Renton, WA 98057–3356; 1414, Revision 03, dated September 15, 2014.
telephone 425–227–1405; fax 425–227–1149. (3) For service information identified in History
Information may be emailed to: 9-ANM-116- this AD, contact Airbus, Airworthiness
AMOC-REQUESTS@faa.gov. Before using Office—EIAS, 1 Rond Point Maurice
On September 24, 2015, a final rule
any approved AMOC, notify your appropriate Bellonte, 31707 Blagnac Cedex, France; was published in the Federal Register
principal inspector, or lacking a principal telephone +33 5 61 93 36 96; fax +33 5 61 establishing Class E airspace at the
inspector, the manager of the local flight 93 44 51; email account.airworth-eas@ Newberry VOR/DME, Newberry, MI (80
standards district office/certificate holding airbus.com; Internet http://www.airbus.com. FR 57522) Docket No. FAA–2015–1869.
district office. The AMOC approval letter (4) You may view this service information Subsequent to publication, the FAA
must specifically reference this AD. at the FAA, Transport Airplane Directorate, found that the exclusionary language for
(2) Required for Compliance (RC): If any 1601 Lind Avenue SW., Renton, WA. For Federal airways and Canadian airspace
service information contains procedures or information on the availability of this noted in the airspace description is not
mstockstill on DSK4VPTVN1PROD with RULES
tests that are identified as RC, those material at the FAA, call 425–227–1221.
procedures and tests must be done to comply (5) You may view this service information
required and, therefore, is removed.
with this AD; any procedures or tests that are that is incorporated by reference at the Final Rule Correction
not identified as RC are recommended. Those National Archives and Records
procedures and tests that are not identified Administration (NARA). For information on Accordingly, pursuant to the
as RC may be deviated from using accepted the availability of this material at NARA, call authority delegated to me, in the
methods in accordance with the operator’s 202–741–6030, or go to: http://www.archives. Federal Register of September 24, 2015,
maintenance or inspection program without gov/federal-register/cfr/ibr-locations.html. (80 FR 57522) FR Doc. 2015–23987, on
VerDate Sep<11>2014 23:14 Nov 23, 2015 Jkt 238001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\24NOR1.SGM 24NOR1](https://thefederalregister.org/doc/80_FR_73325/page/5.svg)
Document Created: 2015-12-14 14:09:20
Document Modified: 2015-12-14 14:09:20
| 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 becomes effective December 29, 2015. | |
| 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 | 80 FR 73099 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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