Airworthiness Directives; Airbus Airplanes, 79738-79742 [2015-30822]

Download as PDF 79738 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules (j) Model 767–300 and –300F Series Airplane Modification For airplanes identified in paragraph (c)(4) of this AD: Within 16 months after the effective date of this AD, install new operational program software into the FCCs, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–22–0146, Revision 1, dated June 25, 2015. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (k) Credit for Actions Accomplished in Accordance With Previous Service Information (1) 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 Boeing Special Attention Service Bulletin 767–22–0143, dated March 6, 2015. (2) This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 767–22–0146, dated March 24, 2015. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (m)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (l)(4)(i) and (l)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 (m) Related Information (1) For more information about this AD, contact Fnu Winarto, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6659; fax: 425– 917–6590; email: fnu.winarto@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone: 206– 544–5000, extension 1; fax: 206–766–5680; Internet https://www.myboeingfleet.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. Issued in Renton, Washington, on December 8, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–32055 Filed 12–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0006; Directorate Identifier 2013–NM–147–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) for all Airbus Model A330–200, A330– 200 Freighter, A330–300, A340–200, and A340–300 series airplanes. The NPRM proposed to require inspecting certain trimmable horizontal stabilizer actuators (THSAs) to determine the number of total flight cycles the THSA has accumulated, and replacing the THSA if necessary. The NPRM was prompted by the results of endurance qualification tests on the THSA, which revealed a partial loss of the no-back brake (NBB) efficiency in specific load conditions. This action revises the NPRM by adding airplanes to the proposed applicability, reducing the proposed compliance times for replacing affected THSAs, and revising the definition of a serviceable THSA. We are proposing this supplemental NPRM (SNPRM) to detect and correct SUMMARY: PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 premature wear of the carbon friction disks on the NBB of the THSA, which could lead to reduced braking efficiency in certain load conditions, and, in conjunction with the inability of the power gear train to keep the ball screw in its last commanded position, could result in uncommanded movements of the trimmable horizontal stabilizer and loss of control of the airplane. Since these actions impose an additional burden over those proposed in the NPRM, we are reopening the comment period to allow the public the chance to comment on these proposed changes. DATES: We must receive comments on this SNPRM by February 8, 2016. 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 proposed AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0006; 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 Office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. E:\FR\FM\23DEP1.SGM 23DEP1 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; 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–2014–0006; Directorate Identifier 2013–NM–147–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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 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 A330–200, A330–200 Freighter, A330–300, A340– 200, and A340–300 series airplanes. The NPRM published in the Federal Register on February 3, 2014 (79 FR 6104). The NPRM was prompted by the results of endurance qualification tests on the THSA, which revealed a partial loss of the NBB efficiency in specific load conditions. The NPRM proposed to require inspecting certain THSAs to determine the number of total flight cycles the THSA had accumulated, and replacing the THSA if necessary. Actions Since Previous NPRM (79 FR 6104, February 3, 2014) was Issued Since we issued the NPRM (79 FR 6104, February 3, 2014), we have determined that additional airplanes are affected by the unsafe condition, the proposed compliance times for replacing affected THSAs should be reduced, and the definition of a serviceable THSA should be revised. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0257R1, dated May 29, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 an unsafe condition on all Airbus Model A330–200, A330–200 Freighter, A330– 300, A340–200, and A340–300 series airplanes; and Model A340–500 and A340–600 series airplanes. The MCAI states: During endurance qualification tests on Trimmable Horizontal Stabilizer Actuator (THSA) of another Airbus aeroplane type, a partial loss of the no-back brake (NBB) efficiency was experienced. Due to THSA design similarity on the A330/A340 fleet, a similar partial loss of the NBB efficiency was identified on THSA Part Number (P/N) 47147 as installed on A330–300 and A340–200/-300 aeroplanes, on THSA P/N 47172 as installed on A330–200/-300 and A340–200/-300 aeroplanes, and on THSA P/N 47175 as installed on A340–500/600 aeroplanes. Investigation results concluded that this partial loss of braking efficiency in some specific aerodynamic load conditions was due to polishing and auto-contamination of the NBB carbon friction disks. This condition, if not detected and corrected and in conjunction with the power gear train not able to keep the ball screw in its last commanded position, could lead to uncommanded movements of the THS, possibly resulting in loss of control of the aeroplane. To address this potential unsafe condition, EASA issued AD 2013–0144 [http://ad.easa. europa.eu/blob/easa_ad_2013_0144.zip/AD_ 2013–0144R1_2] to require replacement of each THSA that has exceeded 16,000 flight cycles (FC) in service, to be sent in shop for NBB carbon disk replacement. Since that AD was issued, a need for clarification has been demonstrated, regarding the identification of the THSA ‘affected’ by this requirement. For this reason, EASA AD 2013–0144 [http://ad.easa.europa.eu/blob/easa_ad_ 2013_0144.zip/AD_2013-0144R1_2] was revised, confirming that this AD only affected those THSA identified by Part Number (P/N) in Airbus Alert Operator Transmission (AOT) A27L005–13. In addition, a note was added to make clear that the life limits as specified in the current revision of ALS Part 4 are still relevant for the affected THSA, as applicable to aeroplane model and THSA P/N. Since EASA AD 2013–0144R1 [http://ad. easa.europa.eu/ad/2013-0144R1] was issued, further assessment of the ageing/endurance issue has resulted in the conclusion that there is a need to replace the NBB installed on the THSA. Consequently, EASA issued AD 2014–0257 [http://ad.easa.europa.eu/blob/EASA_AD_ 2014_0257_R1.pdf/AD_2014-0257R1_1] which retained the requirements of EASA AD 2013–0144R1, which was superseded, and required removal from service of affected THSA. THSA should be sent in shop for NBB carbon disk replacement. This [EASA] AD affected additional THSA P/Ns when compared to EASA AD 2013–0144R1 and Airbus AOT A27L005–13. Since that [EASA] AD was issued, it was determined that it is necessary to consider that the THSA removal for NBB disks replacement could also be calculated since last NBB disk replacement which was done in-shop. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 79739 This proposed AD also adds Model A340–541 and A340–642 airplanes to the applicability. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/# !documentDetail;D=FAA-2014-00060002. Related Service Information Under 1 CFR part 51 Airbus has issued the following service information, dated July 15, 2014. • Service Bulletin A330–27–3199 (for Model A330 series airplanes); • Service Bulletin A340–27–4190 (for Model A340–200 and –300 series airplanes); and • Service Bulletin A340–27–5062 (for Model A340–500 and –600 series airplanes). The service information describes procedures for inspecting the THSA to determine the part number and replacing THSAs having certain part numbers with a new or serviceable part. 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 NPRM. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comments received. The following presents the comments received on the NPRM (79 FR 6104, February 3, 2014) and the FAA’s response to each comment. One commenter, Chris Vargas, supported the intent of the NPRM (79 FR 6104, February 3, 2014). Another commenter, Cameron Lane, restated the proposed costs and unsafe condition. We infer that this commenter supported the intent of the NPRM. Request To Revise THSA Life Limits US Airways stated that there is a conflict between the THSA life limits included in the NPRM (79 FR 6104, February 3, 2014) and the life limits included in the A330 Airworthiness Limitations. The commenter conveyed that it is concerned that operators would be unsure which life limits to follow. We infer that the commenter is requesting that the THSA life limits specified in the NPRM match those specified in the A330 Airworthiness Limitations. The THSA life limits specified in this SNPRM are more restrictive than the life limits specified in the A330 Airworthiness Limitations for the parts identified in paragraphs (g)(1) and (g)(2) of this proposed AD. This SNPRM proposes to require a one-time E:\FR\FM\23DEP1.SGM 23DEP1 79740 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules replacement of an affected THSA with a serviceable part. Serviceable parts identified in paragraphs (g)(1) and (g)(2) of this proposed AD must not exceed the limits proposed in this SNPRM. Any serviceable part not identified in paragraph (g)(1) or (g)(2) of this proposed AD is subject to the life limits and maintenance tasks in the A330 Airworthiness Limitations. We have been notified by Airbus that the NBB life limits will be reduced in a revised Airworthiness Limitation. We might consider further rulemaking if new airworthiness limitations are issued. No change was made to this proposed AD regarding this issue. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Request To Assign Life Limit to Only the NBB Disks US Airways requested that a life limit be assigned only to the NBB disks (part number FE194–031) and not the entire THSA. The commenter stated that the NBB disks are replaceable in the shop and the AD should not limit the life of the entire THSA. We partially agree with the commenter’s request. EASA has revised MCAI 2014–0257, dated November 27, 2014, to include life limit computations for an affected THSA from the most recent NBB inspection, in addition to the accumulated total flight cycles since the THSA’s first installation on an airplane. The revised MCAI is 2014– 0257R1, dated May 29, 2015. We have revised paragraphs (g), (h)(1), (h)(2), and (h)(3) of this proposed AD accordingly. Request To Reduce the Compliance Time Jennifer Paramski stated that the proposed compliance time in the NPRM (79 FR 6104, February 3, 2014) should be reduced because failure of the THSA is a substantial safety concern. The commenter stated that once the THSA has accumulated 16,000 total flight cycles, the airline has 30 months or 4,000 flight cycles to replace the part, and a lot can happen during that time because the part is sensitive to load conditions. The commenter interpreted the compliance time to replace the THSA as tiered and suggested that some airlines might try to extend the timeframe for THSA replacement because after 4,000 flight cycles from the initial 16,000 flights reached, an airline could argue that it should get an additional 1,500 flight cycles or 12 months to replace the part because of the second tier. The commenter explained that airlines would try to maximize the current part on all airplanes to try to maximize profit. The commenter emphasized that maximizing profits could jeopardize the VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 safety of others, which, if there was an accident, would cause more monetary losses in the long run from lawsuits. We do not agree that the compliance time should be reduced. The thresholds for THSA replacement are not tiered, as stated by the commenter. The replacement threshold is based on the accumulation of total flight cycles as of the effective date of the final rule. An airline cannot exceed the thresholds mandated in a final rule unless it requests an alternative method of compliance, issued by the FAA, using the procedures specified in paragraph (n)(1) of this proposed AD. However, we have clarified the compliance times in this SNPRM by revising paragraph (h) of this proposed AD and including a new paragraph (i). The subsequent paragraphs were redesignated accordingly. FAA’s Determination and Requirements of This SNPRM 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. Certain changes described above expand the scope of the proposed AD (79 FR 6104, February 3, 2014). As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this SNPRM. Explanation of Compliance Times The MCAI requires operators to replace certain THSAs by certain dates. The replacements are done for THSAs exceeding a certain flight cycle limit corresponding to each date. EASA determined that accomplishing the replacements by these dates is necessary in order to address the identified unsafe condition. Therefore, we are also specifying compliance dates in this proposed AD. Explanation of ‘‘RC’’ Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests identified as RC (required for compliance) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and 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 alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. Costs of Compliance We estimate that this proposed AD affects 94 airplanes of U.S. registry. We also estimate that it would take about 3 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $23,970, or $255 per product. In addition, we estimate that any necessary follow-on actions would take about 23 work-hours and would require parts costing up to $722,556, for a cost of up to $724,511 per product. We have no way of determining the number of aircraft that might need this action. 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, E:\FR\FM\23DEP1.SGM 23DEP1 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 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 1. The authority citation for part 39 continues to read as follows: ■ asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2014–0006; Directorate Identifier 2013–NM–147–AD. (a) Comments Due Date We must receive comments by February 8, 2016. VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(7) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A330–201, –202, –203, –223, and –243 airplanes. (2) Model A330–223F and –243F airplanes. (3) Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (4) Model A340–211, –212, and –213 airplanes. (5) Model A340–311, –312, and –313 airplanes. (6) Model A340–541 airplanes. (7) Model A340–642 airplanes. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by the results of endurance qualification tests on the trimmable horizontal stabilizer actuator (THSA), which revealed a partial loss of the no-back brake (NBB) efficiency in specific load conditions. We are issuing this AD to detect and correct premature wear of the carbon friction disks on the NBB of the THSA, which could lead to reduced braking efficiency in certain load conditions, and, in conjunction with the inability of the power gear train unable to keep the ball screw in its last commanded position, could result in uncommanded movements of the trimmable horizontal stabilizer and loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection To Determine THSA Part Number and Accumulated Total Flight Cycles Within 90 days after the effective date of this AD: Inspect the THSA to determine if it has a part number that is specified in paragraph (g)(1) or (g)(2) of this AD, and to determine the total number of flight cycles accumulated since the THSA’s first installation on an airplane, or since the most recent NBB replacement. A review of airplane delivery or maintenance records is acceptable in lieu of this inspection if the part number of the THSA can be conclusively determined from that review. (1) For Model A330–200 Freighter, A330– 200, A330–300, A340–200 and A340–300 series airplanes: Part number (P/N) 47147– 500, 47147–700, 47172–300, 47172–500, 47172–510, or 47172–520. (2) For Model A340–500 and –600 series airplanes: P/N 47175–200, 47175–300, 47175–500, or 47175–520. (h) THSA Replacement for Airbus Model A330–200 Freighter, A330–200, A330–300, A340–200, and A340–300 Series Airplanes For Airbus Model A330–200 Freighter, A330–200, A330–300, A340–200, and A340– 300 series airplanes having a THSA with a PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 79741 part number specified in paragraph (g)(1) of this AD: At the applicable time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, replace each affected THSA with a serviceable THSA, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3199, dated July 15, 2014; or Airbus Service Bulletin A340– 27–4190, dated July 15, 2014; as applicable. Note 1 to paragraphs (h), (i), and (j) of this AD: The THSA life limits specified in Part 4—Aging System Maintenance of the Airbus A330 and A340 Airworthiness Limitations Sections are still relevant, as applicable to airplane model and THSA part number. (1) For a THSA that has accumulated or exceeded 20,000 total flight cycles since the THSA’s first installation on an airplane, or since the most recent NBB replacement, whichever is later, as of the effective date of this AD: Within 6 months after the effective date of this AD. (2) For a THSA that has accumulated or exceeded 16,000 total flight cycles, but less than 20,000 total flight cycles since the THSA’s first installation on an airplane, or since the most recent NBB replacement, whichever is later, as of the effective date of this AD: At the applicable time specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. (i) For Model A330–200 Freighter, A330– 200, and A330–300 series airplanes: Within 12 months after the effective date of this AD but without exceeding 20,000 total flight cycles. (ii) For Model A340–200, and A340–300 series airplanes: Within 12 months after the effective date of this AD but without exceeding 20,000 total flight cycles. (3) For a THSA that has accumulated less than 16,000 total flight cycles since first installation on an airplane, or since the most recent NBB replacement, whichever is later, as of the effective date of this AD: At the applicable time specified in paragraph (i) of this AD. (i) Replacement Times for Airbus Model A330–200 Freighter, A330–200, A330–300, A340–200, and A340–300 Series Airplanes With THSAs Having Less Than 16,000 Total Flight Cycles as of the Effective Date of This AD The requirements of this paragraph apply to Airbus Model A330–200 Freighter, A330– 200, A330–300, A340–200, and A340–300 series airplanes having a THSA with a part number specified in paragraph (g)(1) of this AD that has accumulated less than 16,000 total flight cycles since first installation on an airplane, or since the most recent NBB replacement, whichever is later, as of the effective date of this AD. Not later than the date specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, as applicable: For any THSA having reached or exceeded on that date the corresponding number of total flight cycles as specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, as applicable, replace the THSA with a serviceable unit in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3199, dated July 15, 2014; or Airbus Service Bulletin A340– 27–4190, dated July 15, 2014; as applicable. (1) As of 12 months after the effective date of this AD: The THSA flight-cycle limit E:\FR\FM\23DEP1.SGM 23DEP1 79742 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules (since first installation on an airplane, or since last NBB replacement, whichever occurs later) is 16,000 total flight cycles. (2) As of July 31, 2017: The THSA flightcycle limit (since first installation on an airplane, or since last NBB replacement, whichever occurs later) is 14,000 total flight cycles. (3) As of July 31, 2018: The THSA flightcycle limit (since first installation on an airplane, or since last NBB replacement, whichever occurs later) is 12,000 total flight cycles. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (j) THSA Replacement for Airbus Model A340–500 and –600 Series Airplanes For Airbus Model A340–500 and A340– 600 series airplanes having a THSA with a part number specified in paragraph (g)(2) of this AD: Not later than the date specified in paragraphs (j)(1), (j)(2), (j)(3), and (j)(4) of this AD, as applicable: For any THSA having reached or exceeded on that date the corresponding number of total flight cycles as specified in paragraphs (j)(1), (j)(2), (j)(3), and (j)(4) of this AD, as applicable, replace each affected THSA with a serviceable THSA, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340– 27–5062, dated July 15, 2014. (1) As of the effective date of this AD: The THSA flight-cycle limit (since first installation on an airplane, or since last NBB replacement, whichever occurs later) is 6,000 total flight cycles. (2) As of April 30, 2017: The THSA flightcycle limit (since first installation on an airplane, or since last NBB replacement, whichever occurs later) is 5,200 total flight cycles. (3) As of April 30, 2018: The THSA flightcycle limit (since first installation on an airplane, or since last NBB replacement, whichever occurs later) is 4,400 total flight cycles. (4) As of April 30, 2019: The THSA flightcycle limit (since first installation on an airplane, or since last NBB replacement, whichever occurs later) is 3,500 total flight cycles. (k) THSA Replacement Intervals for All Airbus Airplanes Identified in Paragraph (c) of This AD For any part installed as required by this AD having a part number identified in paragraph (g)(1) or (g)(2) of this AD: From the dates specified in paragraphs (i) and (j) of this AD, as applicable, and prior to exceeding the accumulated number of total flight cycles corresponding to each time, replace each affected THSA with a serviceable part, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. (1) Airbus Service Bulletin A330–27–3199, dated July 15, 2014. (2) Airbus Service Bulletin A340–27–4190, dated July 15, 2014. (3) Airbus Service Bulletin A340–27–5062, dated July 15, 2014. (l) Definition of Serviceable THSA For the purposes of this AD a serviceable THSA is a THSA: VerDate Sep<11>2014 17:28 Dec 22, 2015 Jkt 238001 (1) Having a part number identified in paragraph (g)(1) or (g)(2) of this AD that has not exceeded any of the total accumulated flight cycles identified in paragraphs (i)(1) through (i)(3) of this AD, or paragraphs (j)(1) through (j)(4) of this AD, as applicable; or (2) Having a part number that is not identified in paragraph (g)(1) or (g)(2) of this AD. (m) Parts Installation Limitation From each date specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, and paragraphs (j)(1) through (j)(4) of this AD, as applicable, a THSA having a part number identified in paragraph (g)(1) or (g)(2) of this AD may be installed on any airplane, provided the THSA has not exceeded the corresponding number of accumulated total flight cycles. (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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) 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. PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0257R1, dated May 29, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/# !documentDetail;D=FAA-2014-0006-0002. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 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 October 30, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–30822 Filed 12–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–7526; Directorate Identifier 2014–NM–217–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This proposed AD was prompted by the discovery of corroded circlips in fuel vent protectors (FVP) having a certain part number. This proposed AD would require an inspection to determine the part number and serial number of the FVP, and replacement if necessary. We are proposing this AD to detect and correct corroded circlips. Corroded circlips could lead to failure of the circlips and consequent movement of the FVP, resulting in a reduction of the flame protector capability of the FVP cartridge, which could result in damage to the airplane in case of lightning impact or fire on the ground. DATES: We must receive comments on this proposed AD by February 8, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR SUMMARY: E:\FR\FM\23DEP1.SGM 23DEP1

Agencies

[Federal Register Volume 80, Number 246 (Wednesday, December 23, 2015)]
[Proposed Rules]
[Pages 79738-79742]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30822]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0006; Directorate Identifier 2013-NM-147-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-
200, and A340-300 series airplanes. The NPRM proposed to require 
inspecting certain trimmable horizontal stabilizer actuators (THSAs) to 
determine the number of total flight cycles the THSA has accumulated, 
and replacing the THSA if necessary. The NPRM was prompted by the 
results of endurance qualification tests on the THSA, which revealed a 
partial loss of the no-back brake (NBB) efficiency in specific load 
conditions. This action revises the NPRM by adding airplanes to the 
proposed applicability, reducing the proposed compliance times for 
replacing affected THSAs, and revising the definition of a serviceable 
THSA. We are proposing this supplemental NPRM (SNPRM) to detect and 
correct premature wear of the carbon friction disks on the NBB of the 
THSA, which could lead to reduced braking efficiency in certain load 
conditions, and, in conjunction with the inability of the power gear 
train to keep the ball screw in its last commanded position, could 
result in uncommanded movements of the trimmable horizontal stabilizer 
and loss of control of the airplane. Since these actions impose an 
additional burden over those proposed in the NPRM, we are reopening the 
comment period to allow the public the chance to comment on these 
proposed changes.

DATES: We must receive comments on this SNPRM by February 8, 2016.

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 proposed AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.A330-A340@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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0006; 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 
Office (telephone: 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

[[Page 79739]]


FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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-2014-0006; 
Directorate Identifier 2013-NM-147-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

    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 A330-200, 
A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes. 
The NPRM published in the Federal Register on February 3, 2014 (79 FR 
6104). The NPRM was prompted by the results of endurance qualification 
tests on the THSA, which revealed a partial loss of the NBB efficiency 
in specific load conditions. The NPRM proposed to require inspecting 
certain THSAs to determine the number of total flight cycles the THSA 
had accumulated, and replacing the THSA if necessary.

Actions Since Previous NPRM (79 FR 6104, February 3, 2014) was Issued

    Since we issued the NPRM (79 FR 6104, February 3, 2014), we have 
determined that additional airplanes are affected by the unsafe 
condition, the proposed compliance times for replacing affected THSAs 
should be reduced, and the definition of a serviceable THSA should be 
revised. The European Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Union, has issued 
EASA Airworthiness Directive 2014-0257R1, dated May 29, 2015 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A330-
200, A330-200 Freighter, A330-300, A340-200, and A340-300 series 
airplanes; and Model A340-500 and A340-600 series airplanes. The MCAI 
states:

    During endurance qualification tests on Trimmable Horizontal 
Stabilizer Actuator (THSA) of another Airbus aeroplane type, a 
partial loss of the no-back brake (NBB) efficiency was experienced. 
Due to THSA design similarity on the A330/A340 fleet, a similar 
partial loss of the NBB efficiency was identified on THSA Part 
Number (P/N) 47147 as installed on A330-300 and A340-200/-300 
aeroplanes, on THSA P/N 47172 as installed on A330-200/-300 and 
A340-200/-300 aeroplanes, and on THSA P/N 47175 as installed on 
A340-500/600 aeroplanes.
    Investigation results concluded that this partial loss of 
braking efficiency in some specific aerodynamic load conditions was 
due to polishing and auto-contamination of the NBB carbon friction 
disks.
    This condition, if not detected and corrected and in conjunction 
with the power gear train not able to keep the ball screw in its 
last commanded position, could lead to uncommanded movements of the 
THS, possibly resulting in loss of control of the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2013-
0144 [http://ad.easa.europa.eu/blob/easa_ad_2013_0144.zip/AD_2013-0144R1_2] to require replacement of each THSA that has exceeded 
16,000 flight cycles (FC) in service, to be sent in shop for NBB 
carbon disk replacement.
    Since that AD was issued, a need for clarification has been 
demonstrated, regarding the identification of the THSA `affected' by 
this requirement.
    For this reason, EASA AD 2013-0144 [http://ad.easa.europa.eu/blob/easa_ad_2013_0144.zip/AD_2013-0144R1_2] was revised, confirming 
that this AD only affected those THSA identified by Part Number (P/
N) in Airbus Alert Operator Transmission (AOT) A27L005-13. In 
addition, a note was added to make clear that the life limits as 
specified in the current revision of ALS Part 4 are still relevant 
for the affected THSA, as applicable to aeroplane model and THSA P/
N.
    Since EASA AD 2013-0144R1 [http://ad.easa.europa.eu/ad/2013-0144R1] was issued, further assessment of the ageing/endurance issue 
has resulted in the conclusion that there is a need to replace the 
NBB installed on the THSA.
    Consequently, EASA issued AD 2014-0257 [http://ad.easa.europa.eu/blob/EASA_AD_2014_0257_R1.pdf/AD_2014-0257R1_1] 
which retained the requirements of EASA AD 2013-0144R1, which was 
superseded, and required removal from service of affected THSA. THSA 
should be sent in shop for NBB carbon disk replacement. This [EASA] 
AD affected additional THSA P/Ns when compared to EASA AD 2013-
0144R1 and Airbus AOT A27L005-13.
    Since that [EASA] AD was issued, it was determined that it is 
necessary to consider that the THSA removal for NBB disks 
replacement could also be calculated since last NBB disk replacement 
which was done in-shop.

    This proposed AD also adds Model A340-541 and A340-642 airplanes to 
the applicability. You may examine the MCAI in the AD docket on the 
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-
0006-0002.

Related Service Information Under 1 CFR part 51

    Airbus has issued the following service information, dated July 15, 
2014.
     Service Bulletin A330-27-3199 (for Model A330 series 
airplanes);
     Service Bulletin A340-27-4190 (for Model A340-200 and -300 
series airplanes); and
     Service Bulletin A340-27-5062 (for Model A340-500 and -600 
series airplanes).
    The service information describes procedures for inspecting the 
THSA to determine the part number and replacing THSAs having certain 
part numbers with a new or serviceable part. 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 NPRM.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. The following 
presents the comments received on the NPRM (79 FR 6104, February 3, 
2014) and the FAA's response to each comment.
    One commenter, Chris Vargas, supported the intent of the NPRM (79 
FR 6104, February 3, 2014). Another commenter, Cameron Lane, restated 
the proposed costs and unsafe condition. We infer that this commenter 
supported the intent of the NPRM.

Request To Revise THSA Life Limits

    US Airways stated that there is a conflict between the THSA life 
limits included in the NPRM (79 FR 6104, February 3, 2014) and the life 
limits included in the A330 Airworthiness Limitations. The commenter 
conveyed that it is concerned that operators would be unsure which life 
limits to follow. We infer that the commenter is requesting that the 
THSA life limits specified in the NPRM match those specified in the 
A330 Airworthiness Limitations.
    The THSA life limits specified in this SNPRM are more restrictive 
than the life limits specified in the A330 Airworthiness Limitations 
for the parts identified in paragraphs (g)(1) and (g)(2) of this 
proposed AD. This SNPRM proposes to require a one-time

[[Page 79740]]

replacement of an affected THSA with a serviceable part. Serviceable 
parts identified in paragraphs (g)(1) and (g)(2) of this proposed AD 
must not exceed the limits proposed in this SNPRM. Any serviceable part 
not identified in paragraph (g)(1) or (g)(2) of this proposed AD is 
subject to the life limits and maintenance tasks in the A330 
Airworthiness Limitations. We have been notified by Airbus that the NBB 
life limits will be reduced in a revised Airworthiness Limitation. We 
might consider further rulemaking if new airworthiness limitations are 
issued. No change was made to this proposed AD regarding this issue.

Request To Assign Life Limit to Only the NBB Disks

    US Airways requested that a life limit be assigned only to the NBB 
disks (part number FE194-031) and not the entire THSA. The commenter 
stated that the NBB disks are replaceable in the shop and the AD should 
not limit the life of the entire THSA.
    We partially agree with the commenter's request. EASA has revised 
MCAI 2014-0257, dated November 27, 2014, to include life limit 
computations for an affected THSA from the most recent NBB inspection, 
in addition to the accumulated total flight cycles since the THSA's 
first installation on an airplane. The revised MCAI is 2014-0257R1, 
dated May 29, 2015. We have revised paragraphs (g), (h)(1), (h)(2), and 
(h)(3) of this proposed AD accordingly.

Request To Reduce the Compliance Time

    Jennifer Paramski stated that the proposed compliance time in the 
NPRM (79 FR 6104, February 3, 2014) should be reduced because failure 
of the THSA is a substantial safety concern. The commenter stated that 
once the THSA has accumulated 16,000 total flight cycles, the airline 
has 30 months or 4,000 flight cycles to replace the part, and a lot can 
happen during that time because the part is sensitive to load 
conditions. The commenter interpreted the compliance time to replace 
the THSA as tiered and suggested that some airlines might try to extend 
the timeframe for THSA replacement because after 4,000 flight cycles 
from the initial 16,000 flights reached, an airline could argue that it 
should get an additional 1,500 flight cycles or 12 months to replace 
the part because of the second tier. The commenter explained that 
airlines would try to maximize the current part on all airplanes to try 
to maximize profit. The commenter emphasized that maximizing profits 
could jeopardize the safety of others, which, if there was an accident, 
would cause more monetary losses in the long run from lawsuits.
    We do not agree that the compliance time should be reduced. The 
thresholds for THSA replacement are not tiered, as stated by the 
commenter. The replacement threshold is based on the accumulation of 
total flight cycles as of the effective date of the final rule. An 
airline cannot exceed the thresholds mandated in a final rule unless it 
requests an alternative method of compliance, issued by the FAA, using 
the procedures specified in paragraph (n)(1) of this proposed AD. 
However, we have clarified the compliance times in this SNPRM by 
revising paragraph (h) of this proposed AD and including a new 
paragraph (i). The subsequent paragraphs were redesignated accordingly.

FAA's Determination and Requirements of This SNPRM

    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.
    Certain changes described above expand the scope of the proposed AD 
(79 FR 6104, February 3, 2014). As a result, we have determined that it 
is necessary to reopen the comment period to provide additional 
opportunity for the public to comment on this SNPRM.

Explanation of Compliance Times

    The MCAI requires operators to replace certain THSAs by certain 
dates. The replacements are done for THSAs exceeding a certain flight 
cycle limit corresponding to each date. EASA determined that 
accomplishing the replacements by these dates is necessary in order to 
address the identified unsafe condition. Therefore, we are also 
specifying compliance dates in this proposed AD.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as RC (required for compliance) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and 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 alternative method of compliance (AMOC), provided the 
procedures and tests identified as RC can be done and the airplane can 
be put back in a serviceable condition. Any substitutions or changes to 
procedures or tests identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 94 airplanes of U.S. 
registry.
    We also estimate that it would take about 3 work-hours per product 
to comply with the new basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $0 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $23,970, or $255 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 23 work-hours and would require parts costing up to 
$722,556, for a cost of up to $724,511 per product. We have no way of 
determining the number of aircraft that might need this action.

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,

[[Page 79741]]

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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2014-0006; Directorate Identifier 2013-NM-
147-AD.

(a) Comments Due Date

    We must receive comments by February 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(7) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Model A330-223F and -243F airplanes.
    (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes.
    (4) Model A340-211, -212, and -213 airplanes.
    (5) Model A340-311, -312, and -313 airplanes.
    (6) Model A340-541 airplanes.
    (7) Model A340-642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Reason

    This AD was prompted by the results of endurance qualification 
tests on the trimmable horizontal stabilizer actuator (THSA), which 
revealed a partial loss of the no-back brake (NBB) efficiency in 
specific load conditions. We are issuing this AD to detect and 
correct premature wear of the carbon friction disks on the NBB of 
the THSA, which could lead to reduced braking efficiency in certain 
load conditions, and, in conjunction with the inability of the power 
gear train unable to keep the ball screw in its last commanded 
position, could result in uncommanded movements of the trimmable 
horizontal stabilizer and loss of control of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection To Determine THSA Part Number and Accumulated Total 
Flight Cycles

    Within 90 days after the effective date of this AD: Inspect the 
THSA to determine if it has a part number that is specified in 
paragraph (g)(1) or (g)(2) of this AD, and to determine the total 
number of flight cycles accumulated since the THSA's first 
installation on an airplane, or since the most recent NBB 
replacement. A review of airplane delivery or maintenance records is 
acceptable in lieu of this inspection if the part number of the THSA 
can be conclusively determined from that review.
    (1) For Model A330-200 Freighter, A330-200, A330-300, A340-200 
and A340-300 series airplanes: Part number (P/N) 47147-500, 47147-
700, 47172-300, 47172-500, 47172-510, or 47172-520.
    (2) For Model A340-500 and -600 series airplanes: P/N 47175-200, 
47175-300, 47175-500, or 47175-520.

(h) THSA Replacement for Airbus Model A330-200 Freighter, A330-200, 
A330-300, A340-200, and A340-300 Series Airplanes

    For Airbus Model A330-200 Freighter, A330-200, A330-300, A340-
200, and A340-300 series airplanes having a THSA with a part number 
specified in paragraph (g)(1) of this AD: At the applicable time 
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, replace 
each affected THSA with a serviceable THSA, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3199, 
dated July 15, 2014; or Airbus Service Bulletin A340-27-4190, dated 
July 15, 2014; as applicable.

    Note 1 to paragraphs (h), (i), and (j) of this AD:  The THSA 
life limits specified in Part 4--Aging System Maintenance of the 
Airbus A330 and A340 Airworthiness Limitations Sections are still 
relevant, as applicable to airplane model and THSA part number.

    (1) For a THSA that has accumulated or exceeded 20,000 total 
flight cycles since the THSA's first installation on an airplane, or 
since the most recent NBB replacement, whichever is later, as of the 
effective date of this AD: Within 6 months after the effective date 
of this AD.
    (2) For a THSA that has accumulated or exceeded 16,000 total 
flight cycles, but less than 20,000 total flight cycles since the 
THSA's first installation on an airplane, or since the most recent 
NBB replacement, whichever is later, as of the effective date of 
this AD: At the applicable time specified in paragraphs (h)(2)(i) 
and (h)(2)(ii) of this AD.
    (i) For Model A330-200 Freighter, A330-200, and A330-300 series 
airplanes: Within 12 months after the effective date of this AD but 
without exceeding 20,000 total flight cycles.
    (ii) For Model A340-200, and A340-300 series airplanes: Within 
12 months after the effective date of this AD but without exceeding 
20,000 total flight cycles.
    (3) For a THSA that has accumulated less than 16,000 total 
flight cycles since first installation on an airplane, or since the 
most recent NBB replacement, whichever is later, as of the effective 
date of this AD: At the applicable time specified in paragraph (i) 
of this AD.

(i) Replacement Times for Airbus Model A330-200 Freighter, A330-200, 
A330-300, A340-200, and A340-300 Series Airplanes With THSAs Having 
Less Than 16,000 Total Flight Cycles as of the Effective Date of This 
AD

    The requirements of this paragraph apply to Airbus Model A330-
200 Freighter, A330-200, A330-300, A340-200, and A340-300 series 
airplanes having a THSA with a part number specified in paragraph 
(g)(1) of this AD that has accumulated less than 16,000 total flight 
cycles since first installation on an airplane, or since the most 
recent NBB replacement, whichever is later, as of the effective date 
of this AD. Not later than the date specified in paragraphs (i)(1), 
(i)(2), and (i)(3) of this AD, as applicable: For any THSA having 
reached or exceeded on that date the corresponding number of total 
flight cycles as specified in paragraphs (i)(1), (i)(2), and (i)(3) 
of this AD, as applicable, replace the THSA with a serviceable unit 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3199, dated July 15, 2014; or Airbus Service 
Bulletin A340-27-4190, dated July 15, 2014; as applicable.
    (1) As of 12 months after the effective date of this AD: The 
THSA flight-cycle limit

[[Page 79742]]

(since first installation on an airplane, or since last NBB 
replacement, whichever occurs later) is 16,000 total flight cycles.
    (2) As of July 31, 2017: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 14,000 total flight cycles.
    (3) As of July 31, 2018: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 12,000 total flight cycles.

(j) THSA Replacement for Airbus Model A340-500 and -600 Series 
Airplanes

    For Airbus Model A340-500 and A340-600 series airplanes having a 
THSA with a part number specified in paragraph (g)(2) of this AD: 
Not later than the date specified in paragraphs (j)(1), (j)(2), 
(j)(3), and (j)(4) of this AD, as applicable: For any THSA having 
reached or exceeded on that date the corresponding number of total 
flight cycles as specified in paragraphs (j)(1), (j)(2), (j)(3), and 
(j)(4) of this AD, as applicable, replace each affected THSA with a 
serviceable THSA, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A340-27-5062, dated July 15, 2014.
    (1) As of the effective date of this AD: The THSA flight-cycle 
limit (since first installation on an airplane, or since last NBB 
replacement, whichever occurs later) is 6,000 total flight cycles.
    (2) As of April 30, 2017: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 5,200 total flight cycles.
    (3) As of April 30, 2018: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 4,400 total flight cycles.
    (4) As of April 30, 2019: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 3,500 total flight cycles.

(k) THSA Replacement Intervals for All Airbus Airplanes Identified in 
Paragraph (c) of This AD

    For any part installed as required by this AD having a part 
number identified in paragraph (g)(1) or (g)(2) of this AD: From the 
dates specified in paragraphs (i) and (j) of this AD, as applicable, 
and prior to exceeding the accumulated number of total flight cycles 
corresponding to each time, replace each affected THSA with a 
serviceable part, in accordance with the Accomplishment Instructions 
of the applicable service information identified in paragraphs 
(k)(1), (k)(2), and (k)(3) of this AD.
    (1) Airbus Service Bulletin A330-27-3199, dated July 15, 2014.
    (2) Airbus Service Bulletin A340-27-4190, dated July 15, 2014.
    (3) Airbus Service Bulletin A340-27-5062, dated July 15, 2014.

(l) Definition of Serviceable THSA

    For the purposes of this AD a serviceable THSA is a THSA:
    (1) Having a part number identified in paragraph (g)(1) or 
(g)(2) of this AD that has not exceeded any of the total accumulated 
flight cycles identified in paragraphs (i)(1) through (i)(3) of this 
AD, or paragraphs (j)(1) through (j)(4) of this AD, as applicable; 
or
    (2) Having a part number that is not identified in paragraph 
(g)(1) or (g)(2) of this AD.

(m) Parts Installation Limitation

    From each date specified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD, and paragraphs (j)(1) through (j)(4) of this AD, 
as applicable, a THSA having a part number identified in paragraph 
(g)(1) or (g)(2) of this AD may be installed on any airplane, 
provided the THSA has not exceeded the corresponding number of 
accumulated total flight cycles.

(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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) 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 2014-0257R1, dated May 29, 2015, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2014-0006-0002.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
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 October 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-30822 Filed 12-22-15; 8:45 am]
 BILLING CODE 4910-13-P