Airworthiness Directives; Airbus Airplanes, 57122-57129 [2015-21730]

Download as PDF 57122 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0529; Directorate Identifier 2013–NM–260–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 A318, A319, A320, and A321 series airplanes. The NPRM proposed to supersede Airworthiness Directives (AD) 2011–13–11 and AD 2013–16–09. AD 2011–13–11 currently requires an amendment of the airplane flight manual (AFM), repetitive checks of specific centralized fault display system (CFDS) messages, an inspection of the opening sequence of the main landing gear (MLG) door actuator for discrepancies if certain messages are found, and corrective actions if necessary. AD 2013–16–09 currently requires an inspection to determine airplane configuration and part numbers of the landing gear control interface unit and MLG door actuators; and, for affected airplanes, repetitive inspections of the opening sequence of the MLG door actuator, and replacement of the MLG door actuator if necessary; and provides optional terminating action for the repetitive inspections. The NPRM was prompted by a determination that the interval of the MLG door opening sequence inspection must be reduced. The NPRM proposed to reduce the interval of the MLG door opening sequence inspection, and also to replace or modify certain MLG door actuators. This action revises the NPRM by adding a flushing procedure to be performed when installing a new MLG door actuator. We are proposing this supplemental NPRM (SNPRM) to detect and correct deterioration of the damping ring and associated retaining ring of the MLG door actuator, which can sufficiently increase the friction inside the actuator to restrict opening of the MLG door by gravity, during operation of the landing gear alternate (free-fall) extension system. This condition could prevent the full extension and/or downlocking of the MLG, possibly resulting in MLG collapse during landing and consequent damage to the airplane and Lhorne on DSK5TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 14:51 Sep 21, 2015 Jkt 235001 injury to occupants. 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 November 6, 2015. 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 Airbus service information identified in this proposed 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. For General Electric service information identified in this AD contact GE Aviation, Customer Support Center, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: cs.techpubs@ge.com; Internet: http:// www.geaviation.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– 0529; 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. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0529; Directorate Identifier 2013–NM–260–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 A318, A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on August 13, 2014 (79 FR 47395; corrected August 27, 2014 (79 FR 51117)) (‘‘the NPRM’’). The NPRM proposed to supersede AD 2011–13–11, Amendment 39–16734 (76 FR 37241, June 27, 2011) (‘‘AD 2011–13–11’’); and AD 2013–16–09, Amendment 39–17547 (78 FR 48286, August 8, 2013) (‘‘AD 2013–16–09’’). AD 2011–13–11 currently requires an amendment of the AFM, repetitive checks of specific CFDS messages, an inspection of the opening sequence of the MLG door actuator for discrepancies if certain messages are found, and corrective actions if necessary. AD 2013–16–09 currently requires an inspection to determine airplane configuration and part numbers of the landing gear control interface unit and MLG door actuators; and, for affected airplanes, repetitive inspections of the opening sequence of the MLG door actuator, and replacement of the MLG door actuator if necessary; and provides optional terminating action for the repetitive inspections. The NPRM was prompted by a determination that the interval of the MLG door opening sequence inspection must be reduced. The NPRM proposed to reduce the interval of the MLG door opening E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules sequence inspection, and also to replace or modify certain MLG door actuators. Lhorne on DSK5TPTVN1PROD with PROPOSALS Actions Since Previous NPRM Was Issued Since we issued the NPRM, we have determined that a flushing procedure must be performed when installing a new MLG door actuator. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0221, dated September 30, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on all Airbus Model A318, A319, A320, and A321 series airplanes. The MCAI states: Some operators reported slow operation of the main landing gear (MLG) door opening/ closing sequence, leading to the generation of [electronic centralized aircraft monitor] ECAM warnings during the landing gear retraction or extension sequence. Investigations showed that the damping ring and associated retaining ring of the MLG door actuator may deteriorate. The resultant debris increases the friction inside the actuator which can be sufficiently high to restrict opening of the MLG door by gravity, during operation of the landing gear alternate (freefall) extension system. This condition, if not corrected, could prevent the full extension and/or down locking of the MLG, possibly resulting in MLG collapse during landing or rollout and consequent damage to the aeroplane and injury to occupants. [An EASA AD] was issued [and later revised] to require repetitive inspections of the opening sequence of the MLG door in order to identify the affected actuators, and to introduce as an optional terminating action Airbus production Modification (mod) 38274 and associated [Airbus] Service Bulletin (SB) A320–32–1338, which incorporate an improved retaining ring, located on the piston rod’s extension end, and a new piston rod with machined shoulder to accommodate the thicker section of the modified retaining ring. After in-service introduction of the new MLG door actuator, Part Number (P/N) 114122012 (Post-mod 38274—SB A320–32– 1338), several operators reported failures of internal parts of the MLG door actuator. Investigations confirmed that these failures could result in slow extension of the actuator rod, delaying the MLG door operation, or possibly stopping just before the end of the stroke, preventing the door to reach the fully open position. [An EASA AD], which superseded EASA AD 2006–0112R1 [http://ad.easa.europa.eu/ blob/easa_ad_2006_0112_R1_ superseded.pdf/AD_2006-0112R1_1], was issued [and later revised] to require amendment of the applicable Airplane Flight Manual (AFM), repetitive checks of specific Centralized Fault Display System (CFDS) messages, repetitive inspections of the opening sequence of the MLG door actuator VerDate Sep<11>2014 14:51 Sep 21, 2015 Jkt 235001 and, depending on findings, corrective action(s). Since EASA AD 2011–0069R1 [http:// ad.easa.europa.eu/blob/easa_ad_2011_0069_ R1_superseded.pdf/AD_2011-0069R1_1] was issued, Airbus introduced a reinforced MLG door actuator P/N 114122014 (mod 153655). Airbus issued SB A320–32–1407 containing instructions for in-service replacement of the affected MLG door actuators, or modification of the actuators to the new standard. In addition, following a recent occurrence with a gear extension problem, the result of additional analyses by Airbus revealed that the CFDS expected specific messages may not be generated and as a result, repetitive checks of messages are not effective for aeroplanes fitted with landing gear control interface unit (LGCIU) interlink communication ARINC 429 (applied in production through Airbus mod 39303, or in service through Airbus SB A320–32–1409), in combination with LGCIUs 80–178–02– 88012 or 80–178–03–88013 in both positions and at least one MLG door actuator pre-mod 153655 (pre-Airbus SB A320–32–1407—preGE SB 114122–32–105) installed. Prompted by these findings, EASA issued Emergency AD 2013–0132–E [http:// ad.easa.europa.eu/blob/easa_ad_2013_0132_ E_superseded.pdf/EAD_2013-0132-E_1 (which corresponds to FAA AD 2013–16–09)] to require identification of the affected aeroplanes to establish the configuration and, for those aeroplanes, repetitive inspections of the opening sequence of the MLG door actuator and, depending on findings, replacement of the MLG door actuator. That [EASA] AD also provided an optional terminating action by disconnection of the interlink for certain LGCIUs, or in-service modification of the aeroplane through Airbus SB A320–32–1407 (equivalent to Airbus production mod 153655). Since those ADs (EASA AD 2011–0069R1 and EASA AD 2013–0132–E) were issued, analyses performed by Airbus have revealed that the MLG door opening sequence inspection interval needed to be reduced, and that the (previously optional) terminating action needed to be made mandatory. Prompted by these findings, EASA issued AD 2013–0288 [http://ad.easa.europa.eu/ blob/easa_ad_2013_0288_superseded.pdf/ AD_2013-0288_1], retaining the requirements of EASA AD 2011–0069R1 and EASA AD 2013–0132–E, which were superseded, but with reduced inspection intervals, and to require replacement or modification, as applicable, of the affected MLG door actuators as terminating action to the monitoring and repetitive checks and inspections. Following introduction of post-mod 153655 MLG door actuators on in-service aeroplanes, it has been observed that, in case the removed pre-mod MLG door actuator has internal damage, contamination of the hydraulic system could have occurred. This condition, if not detected and corrected, could result in performance degradation (damping degradation) of the post-mod MLG door actuator. Testing performed with a new actuator tested in heavily contaminated hydraulic system did PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 57123 not show abnormal hydraulic Restriction/ blockage. It is thus not requested to perform this ‘‘flushing procedure’’ on aircraft already retrofitted with std-14 actuators. In addition, since EASA AD 2013–0288 was issued, the applicable AFM was revised and repetitive checks of specific CFDS messages are no longer considered to be required, due to the reduced intervals required by EASA AD 2013–0288. For the reasons described above, this [EASA] AD partially retains the requirements of EASA AD 2013–0288, which is superseded, introduces improved wording for clarification and requires, in addition to the revised operational (AFM) procedure, hydraulic flushing prior to any installation of a post-mod MLG door actuator. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-5290003. Related Service Information Under 1 CFR part 51 Airbus has issued Service Bulletins A320–32–1390, Revision 03, dated July 3, 2014; and A320–32–1407, Revision 01, dated July 3, 2014. Airbus has also issued A318/A319/A320/A321 Temporary Revision (TR) TR437, L/G GEAR NOT DOWNLOCKED, Issue 1.0, dated May 23, 2014, to the Airplane Flight Manual (AFM). Airbus Service Bulletin A320–32– 1390, Revision 03, dated July 3, 2014, describes procedures for inspecting the operation of the MLG door opening sequence to determine if an actuator is defective, flushing contamination from the landing gear extension and retraction system (LGERS), and replacing the door actuator if necessary. Airbus Service Bulletin A320–32– 1407, Revision 01, dated July 3, 2014, describes procedures for flushing contamination from the LGERS, and installing new MLG door actuators. Airbus A318/A319/A320/A321 TR TR437, L/G GEAR NOT DOWNLOCKED, Issue 1.0, dated May 23, 2014, to the AFM updates the procedure used for incomplete landing gear extension during approach. General Electric Service Bulletin 114122–32–105, Revision 2, dated June 24, 2014, describes procedures for conversion of a MLG door actuator and to remove unwanted material from the hydraulic fluid route. 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 SNPRM. E:\FR\FM\22SEP1.SGM 22SEP1 57124 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules Comments We gave the public the opportunity to participate in developing this SNPRM. We considered the comments received. Requests To Adopt the Actions of EASA Airworthiness Directive 2014–0221, Dated September 30, 2014, and Certain Service Bulletins Airbus requested that we revise the NPRM to adopt the requirements of EASA Airworthiness Directive 2014– 0221, dated September 30, 2014; Airbus Service Bulletin A320–32–1390, Revision 03, dated July 3, 2014; and Airbus Service Bulletin A320–32–1407 Revision 01, dated July 3, 2014. Airbus stated that EASA issued a global airplane flight manual (AFM) TR to mandate updated operational procedures. US Airways requested that we reference Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014, and a new AFM procedure referenced in ‘‘FOT 999–0032/14.’’ We agree with the commenters’ requests. EASA Airworthiness Directive 2014–0221, dated September 30, 2014, requires, among other things, a revised operational AFM procedure, and hydraulic flushing prior to any installation of a post-modification MLG door actuator. We have revised paragraphs (j), (k), (l), (m), and (w) as designated in the NPRM (paragraphs (j), (k), (l), (m), and (x) in this SNPRM)) to reference Airbus Service Bulletin A320– 32–1390, Revision 03, dated July 3, 2014; and paragraphs (r), (t), (u), (w), and (x) as designated in the NPRM (paragraphs (r), (u), (v), (x), and (y) in this SNPRM)) to reference Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014; as the appropriate sources of service information for accomplishing the proposed actions. Lhorne on DSK5TPTVN1PROD with PROPOSALS Request To Not Mandate the Actions in Airbus Service Bulletin A320–32–1407, Revision 01, Dated July 3, 2014 United Airlines requested that we not require the actions in Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014. United Airlines stated that Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014, recommends that operators flush the affected hydraulic system. United Airlines stated that it disagrees with this proposed action and explained that Airbus instituted this requirement to flush the hydraulic system as it failed to recommend the removal, inspection, and cleaning of the restrictors during the modification of the MLG door actuator to the part number (P/N) 114122014 configuration. United VerDate Sep<11>2014 14:51 Sep 21, 2015 Jkt 235001 Airlines also stated that it has opted to overhaul the MLG door actuators as well as perform the modification described in Airbus Service Bulletin A320–32– 1407, dated May 14, 2013. United Airlines explained that this overhaul requires that the restrictors (P/N 114122233 and P/N 114122232) and transfer pipe be removed, inspected, and cleaned. United Airlines stated that it is of the opinion that flushing the hydraulic system is not required as there is no contamination present in the restrictors or the transfer pipe. We disagree with the commenter’s request. Airbus informed the FAA that debris can leave the damaged actuator and remain in the hydraulic lines connected to the door actuator. Flushing of the hydraulic system is required to prevent debris from entering the new actuator. If debris enters the new actuator, its performance can be affected. The flow rate during normal operation is insufficient to ensure complete flushing of the debris to the hydraulic low pressure filter within a few door cycles. Therefore, a specific maintenance procedure has been defined and introduced in Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014; and General Electric Service Bulletin 114122–32–105, Revision 2, dated June 24, 2014. EASA has issued AD 2014– 0221, dated September 30, 2014, requiring flushing of the affected hydraulic system in accordance with Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014. Request To Provide Credit for Previous Actions US Airways requested that we provide credit for the actions required by paragraphs (t) and (u) of the proposed AD (paragraphs (u) and (v) of this SNPRM)), if those actions were done before the effective date of the AD using Airbus Service Bulletins A320– 32–1407, dated May 14, 2013, or Revision 01, dated July 3, 2014; or General Electric Service Bulletin 114122–32–105, dated January 17, 2013. We partially agree with the commenter’s request. In this SNPRM, paragraph (aa) already provides credit for General Electric Service Bulletin 114122–32–105, dated January 17, 2013, for the actions in paragraphs (u) and (v) done prior to the effective date of the final rule. We do not agree with giving credit for Airbus Service Bulletin A320– 32–1407, dated May 14, 2013; or Revision 01, dated July 3, 2014; because those service bulletins do not require flushing the hydraulic system prior to the installation of P/N 114122014. We PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 have not changed the proposed AD in this regard. 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 NPRM. 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 ‘‘RC’’ Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directives 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 Required for Compliance (RC) 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 Airbus service information, procedures and tests identified as RC 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 E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules identified as RC will require approval of an AMOC. Changes to the Proposed AD This SNPRM makes the following changes to the NPRM. We have moved the credit for Airbus Service Bulletin A320–32–1309, dated March 7, 2006, specified in paragraph (g) of AD 2011–13–11, into paragraph (aa)(1) of the proposed AD. We have reformatted and redesignated three tables as figures to comply with requirements of the Office of the Federal Register, as follows: • ‘‘Table 1 to Paragraph (p) of this AD—Affected Part Numbers’’ is ‘‘Figure 2 to Paragraph (p) of this AD—Affected Part Numbers;’’ • ‘‘Table 2 to Paragraph (v) of this AD—Affected Part Numbers’’ is ‘‘Figure 3 to Paragraph (v) of this AD—Affected Part Numbers;’’ and • ‘‘Table 3 to Paragraph (z) of this AD—Affected Part Numbers’’ is ‘‘Figure 4 to Paragraph (z) of this AD.’’ Lhorne on DSK5TPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this SNPRM affects 953 airplanes of U.S. registry. The actions that are required by AD 2011–13–11, and retained in this SNPRM, take about 7 work-hours per product, per inspection cycle, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2011–13–11 is $595 per product. The actions that are required by AD 2013–16–09, and retained in this SNPRM, take about 3 work-hours per product, per inspection cycle, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2013–16–09 is $255 per product. We also estimate that it would take about 19 work-hours per product to comply with the basic requirements of this SNPRM. The average labor rate is $85 per work-hour. Required parts would cost about $17,140 per product. Based on these figures, we estimate the cost of this SNPRM on U.S. operators to be $17,873,515, or $18,755 per product. In addition, we estimate that any necessary follow-on actions would take about 3 work-hours, for a cost of $255 per product. We have no way of determining the number of aircraft that might need these actions. detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. Authority for This Rulemaking § 39.13 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 ■ ■ VerDate Sep<11>2014 14:51 Sep 21, 2015 Jkt 235001 [Amended] 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directives (AD) 2011–13–11, Amendment 39– 16734 (76 FR 37241, June 27, 2011) (‘‘AD 2011–13–11’’); and AD 2013–16– 09, Amendment 39–17547 (78 FR PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 57125 48286, August 8, 2013) (‘‘AD 2013–16– 09’’); and ■ b. Adding the following new AD: Airbus: Docket No. FAA–2014–0529; Directorate Identifier 2013–NM–260–AD. (a) Comments Due Date We must receive comments by November 6, 2015. (b) Affected ADs This AD replaces AD 2011–13–11, Amendment 39–16734 (76 FR 37241, June 27, 2011) (‘‘AD 2011–13–11’’); and AD 2013– 16–09, Amendment 39–17547 (78 FR 48286, August 8, 2013) (‘‘AD 2013–16–09’’). (c) Applicability This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, all manufacturer serial numbers. (1) Model A318–111, –112, –121, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by a determination that the inspection interval of the main landing gear (MLG) door opening sequence must be reduced. We are issuing this AD to detect and correct deterioration of the damping ring and associated retaining ring of the MLG door actuator, which can sufficiently increase the friction inside the actuator to restrict opening of the MLG door by gravity, during operation of the landing gear alternate (free-fall) extension system. This condition could prevent the full extension and/or down-locking of the MLG, possibly resulting in MLG collapse during landing and consequent damage to the aeroplane and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections/ Replacement, With a Formatting Change This paragraph restates the requirements of paragraph (g) of AD 2011–13–11, with a formatting change. At the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable: Do a general visual inspection of the operation of the MLG door opening sequence to determine if a defective actuator is installed by doing all the applicable actions, including replacing the door actuator, as applicable, specified in the Accomplishment Instructions of Airbus Service Bulletin A320–32–1309, Revision 01, dated June 19, 2006. Do all applicable replacements before further flight. Repeat the inspection thereafter at intervals not to exceed 900 flight cycles. Doing the E:\FR\FM\22SEP1.SGM 22SEP1 57126 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules inspection required by paragraph (l) of this AD terminates the requirements of this paragraph. (1) For airplanes on which a record of the total number of flight cycles on the MLG door actuator is available: Before the accumulation of 3,000 total flight cycles on the MLG door actuator, or within 800 flight cycles after April 27, 2007 (the effective date of AD 2007–06–18, Amendment 39–14999 (72 FR 13681, March 23, 2007)), whichever is later. (2) For airplanes on which a record of the total number of flight cycles on the MLG door actuator is not available: Within 800 flight cycles after April 27, 2007 (the effective date of AD 2007–06–18). (3) For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ (h) Retained Provision Regarding Reporting/ Parts Return, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2011–13–11, with no changes. Although the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1309, Revision 01, dated June 19, 2006, specify submitting certain information to the manufacturer and sending defective actuators back to the component manufacturer for investigation, this AD does not include those requirements. (i) Retained Revision of the Airplane Flight Manual (AFM), With Formatting Changes This paragraph restates the requirements of paragraph (i) of AD 2011–13–11, with formatting changes. Within 14 days after July 12, 2011 (the effective date of AD 2011–13– 11), revise the Emergency Procedure Section of the AFM to incorporate the information in figure 1 to paragraph (i) of this AD. This may be done by inserting a copy of this AD into the AFM. When a statement identical to that in figure 1 to paragraph (i) of this AD has been included in the Emergency Procedure Section of the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. Doing the actions required by paragraph (t) of this AD terminates the requirements of this paragraph. FIGURE 1 TO PARAGRAPH (I) OF THIS AD—AFM REVISION Lhorne on DSK5TPTVN1PROD with PROPOSALS • If ECAM triggers the ‘‘L/G GEAR NOT DOWNLOCKED’’ warning, apply the following procedure: Recycle landing gear. • If unsuccessful after 2 min: Extend landing gear by gravity. Refer to ABN–32 L/G GRAVITY EXTENSION. (j) Retained Repetitive Checks, With New Optional Actions and New Service Information This paragraph restates the requirements of paragraph (j) of AD 2011–13–11, with new optional actions and new service information. Within 14 days after July 12, 2011 (the effective date of AD 2011–13–11), or before the accumulation of 800 total flight cycles, whichever occurs later, check the post flight report (PFR) for centralized fault display system (CFDS) messages triggered within the last 8 days, in accordance with paragraph 4.2.1 of Airbus All Operators Telex (AOT) A320–32A1390, dated February 10, 2011. Repeat the check thereafter at intervals not to exceed 8 days or 5 flight cycles, whichever occurs later. If done in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, the use of an alternative method to check the PFR for CFDS messages (e.g., AIRMAN) is acceptable in lieu of this check if the messages can be conclusively determined from that method. Repetitive inspections of the door opening sequence of the left-hand (LH) and right-hand (RH) doors of the MLG, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014, are an acceptable method of compliance for the actions required by this paragraph. Repetitive inspections of the door opening sequence of the LH and RH doors of the MLG of an airplane, as required by paragraph (p) of this AD, is an acceptable method to comply with the requirements of this paragraph. (k) Retained On-Condition Inspection, With New Service Information This paragraph restates the requirements of paragraph (k) of AD 2011–13–11, with new service information. If, during any check VerDate Sep<11>2014 14:51 Sep 21, 2015 Jkt 235001 required by paragraph (j) of this AD, a pair of specific CFDS messages specified in paragraph 4.2.1 of Airbus AOT A320– 32A1390, dated February 10, 2011, has been triggered by both landing gear control and indication units (LGCIU) for the same flight, before further flight, inspect the door opening sequence of the affected doors of the MLG for discrepancies (i.e., if any condition specified in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT A320–32A1390, dated February 10, 2011, is not met; or if any door actuator fails any inspection check specified in Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014). Do the inspection in accordance with paragraph 4.2.2 of Airbus AOT A320–32A1390, dated February 10, 2011; or the Accomplishment Instructions of Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014. As of the effective date of this AD, use only Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014, for the actions required by this paragraph. (l) Retained Repetitive Inspections, With New Service Information, New Optional Actions, and Reduced Compliance Times This paragraph restates the requirements of paragraph (l) of AD 2011–13–11, with new service information, new optional actions, and reduced compliance times. At the applicable time specified in paragraph (l)(1) or (l)(2) of this AD: Inspect the door opening sequence of the LH and RH doors of the MLG for discrepancies (i.e., if any condition specified in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT A320–32A1390, dated February 10, 2011, is not met; or if any door actuator fails any inspection check specified in the Accomplishment Instructions of Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014). Do the inspection in accordance with the PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 instructions of paragraph 4.2.2 of Airbus AOT A320–32A1390, dated February 10, 2011; or the Accomplishment Instructions of Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014. As of the effective date of this AD, use only Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014, for the actions required by this paragraph. Repeat the inspection within 8 days or 5 flight cycles after the effective date of this AD, whichever occurs later, without exceeding 425 flight cycles since the most recent inspection; and thereafter repeat the inspection at intervals not to exceed 8 days or 5 flight cycles, whichever occurs later. In addition, whenever any airplane is not operated for a period longer than 8 days, do the inspection before further flight. Doing this inspection terminates the requirements of paragraph (g) of this AD. Repetitive inspections of the door opening sequence of the LH and RH doors of the MLG of an airplane, as required by paragraph (p) of this AD, is an acceptable method to comply with the requirements of this paragraph. (1) For airplanes on which an inspection required by paragraph (g) of this AD has been done as of July 12, 2011 (the effective date of AD 2011–13–11): Within 800 flight cycles after doing the most recent inspection required by paragraph (g) of this AD, or within 100 flight cycles after July 12, 2011, whichever occurs later. (2) For airplanes on which an inspection required by paragraph (g) of this AD has not been done as of July 12, 2011 (the effective date of AD 2011–13–11): Within 800 flight cycles after July 12, 2011. (m) Retained Replacement, With New Service Information This paragraph restates the requirements of paragraph (m) of AD 2011–13–11, with new E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules service information. If any discrepancy (i.e., if any condition specified in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT A320– 32A1390, dated February 10, 2011, is not met; or if any door actuator fails any inspection check specified in the Accomplishment Instructions of Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014) is found during any inspection required by paragraph (k) or (l) of this AD, before further flight, replace the affected MLG door actuator with a new MLG door actuator, in accordance with the instructions of Airbus AOT A320–32A1390, dated February 10, 2011; or Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014. As of the effective date of this AD, use only Airbus Service Bulletin A320– 32–1390, Revision 03, dated July 13, 2014, to do the actions required by this paragraph. (n) Retained Statement of No Terminating Action for Certain Requirements, With No Changes This paragraph restates the statement of paragraph (n) of AD 2011–13–11, with no changes. Replacement of the MLG door actuator as required by paragraph (m) of this AD is not a terminating action for the repetitive actions required by paragraphs (j) and (l) of this AD. Lhorne on DSK5TPTVN1PROD with PROPOSALS (o) Retained Configuration and Part Number Determination, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2013–16–09, with no changes. At the later of the compliance times specified in paragraphs (o)(1) and (o)(2) of this AD: Do an inspection to determine the configuration (modification status) of the airplane and identify the part number of the LH and RH LGCIU and MLG door actuators. A review of the airplane delivery or maintenance records is acceptable for compliance with the requirements of this paragraph provided the airplane configuration and installed components can be conclusively determined from that review. (1) Prior to the accumulation of 800 total flight cycles since first flight of the airplane. (2) Within 14 days after August 23, 2013 (the effective date of AD 2013–16–09). (p) Retained MLG Door Opening Sequence Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2013–16–09, with no changes. If, during the determination and identification required by paragraph (o) of this AD, the configuration of the airplane is determined to be post-Airbus Modification 39303 or post-Airbus Service Bulletin A320– 32–1409 (Interlink Communication ARINC 429 installed), and both an LGCIU and a MLG door actuator are installed with a part number listed in figure 2 to paragraph (p) of this AD: Except as provided by paragraph (s) of this AD, at the later of the compliance times specified in paragraphs (o)(1) and (o)(2) of this AD, and thereafter at intervals not to exceed 8 days or 5 flight cycles, whichever occurs later, do an inspection of the door opening sequence of the LH and RH MLG doors, in accordance with the instructions of Airbus AOT A32N001–13, dated June 24, 2013. VerDate Sep<11>2014 14:51 Sep 21, 2015 Jkt 235001 FIGURE 2 TO PARAGRAPH (P) OF THIS AD—AFFECTED PART NUMBERS Component name LGCIU (LH and RH) MLG door actuator ... Part number 80–178–02–88012 80–178–03–88013 114122006 114122007 114122009 114122010 114122011 114122012 (q) Retained MLG Door Opening Sequence Corrective Action, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2013–16–09, with no changes. If a slow door operation or restricted extension is found during any inspection required by paragraph (p) of this AD: Before further flight, replace the affected MLG door actuator with a new or serviceable actuator, in accordance with the instructions of Airbus AOT A32N001–13, dated June 24, 2013. (r) Retained Terminating Action Limitation for Certain Actions, With New Service Information This paragraph restates the requirements of paragraph (j) of AD 2013–16–09, with new service information. Replacement of a MLG door actuator, as required by paragraph (q) of this AD, does not constitute terminating action for the repetitive inspections required by paragraph (p) of this AD, unless MLG door actuators having P/N 114122014 are installed on both LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1407, dated May 14, 2013; or Airbus Service Bulletin A320– 32–1407, Revision 01, dated July 3, 2014. As of the effective date of this AD, use only Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014, for the actions required by this paragraph. (s) Retained Repetitive Inspection Exception, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2013–16–09, with no changes. Airplanes on which the LGCIU interlink is disconnected (Airbus Modification 155522 applied in production, or modified in-service in accordance with the instructions of Airbus AOT A32N001–13, dated June 24, 2013), or on which MLG door actuators having P/N 114122014 are installed on both LH and RH sides (Airbus Modification 153655 applied in production, or modified in-service as described in Airbus Service Bulletin A320–32–1407), are not required to do the actions required by paragraph (p) of this AD, provided that the airplane is not modified to a configuration as defined in paragraph (p) of this AD. (t) New Revision of the AFM Within 14 days after the effective date of this AD, revise the Emergency Procedure Section of the AFM to incorporate Airbus A318/A319/A320/A321 Temporary Revision (TR) TR437, L/G GEAR NOT DOWNLOCKED, Issue 1.0, dated May 23, 2014. When this TR has been included in general revisions of the AFM, the general PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 57127 revisions may be inserted in the AFM, provided the relevant information in the general revision is identical to that in this TR, and the copy of this TR may be removed from the AFM. Doing the action required by this paragraph terminates the actions required by paragraph (i) of this AD. (u) New Replacement of MLG Door Actuator Having P/N 114122012 Within 12 months after the effective date of this AD: Replace each MLG door actuator having P/N 114122012 with a MLG door actuator having P/N 14122014, and flush the affected hydraulic system, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014; or modify each actuator, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of General Electric Service Bulletin 114122–32–105, Revision 2, dated June 24, 2014; except where General Electric Service Bulletin 114122–32–105, Revision 2, dated June 24, 2014, specifies to contact the manufacturer, before further flight, repair 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). (v) New Replacement of Certain Other MLG Door Actuators Within 24 months after the effective date of this AD: Replace each MLG door actuator having a part number listed in figure 3 to paragraph (v) of this AD, except P/N 114122012, with a MLG door actuator having P/N 14122014, and flush the affected hydraulic system, in accordance with Accomplishment Instructions of Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014; or modify each actuator, including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of General Electric Service Bulletin 114122–32–105, Revision 2, dated June 24, 2014; except where General Electric Service Bulletin 114122–32–105, Revision 2, dated June 24, 2014, specifies to contact the manufacturer, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. FIGURE 3 TO PARAGRAPH (V) OF THIS AD—AFFECTED PART NUMBERS Component name MLG door actuator ................. Part number 114122006 114122007 114122009 114122010 114122011 114122012 (w) New Terminating Action Modification of an airplane as required by paragraphs (u) and (v) of this AD, as applicable, constitutes terminating action for E:\FR\FM\22SEP1.SGM 22SEP1 57128 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules all repetitive actions (PFR monitoring checks and inspections) required by this AD for that airplane. (x) New Conditional Terminating Action Replacement of a MLG door actuator as required by paragraphs (m) and (q) of this AD; or corrective actions as specified in Airbus AOT A320–32A1390, dated February 10, 2011; or replacement of a MLG door actuator as specified in Airbus Service Bulletin A320–32–1390, Revision 03, dated July 13, 2014; does not constitute terminating action for the repetitive inspections required by paragraphs (j), (l), and (p) of this AD, unless MLG door actuators having P/N 114122014 are installed on both LH and RH sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1407, Revision 01, dated July 3, 2014. (y) New Exception to AD Requirements (1) An airplane on which MLG door actuators having P/N 114122014 are installed on both LH and RH sides (Airbus Modification 153655 applied in production, or modified in service as specified in Airbus Service Bulletin A320–32–1407, dated May 14, 2013; Airbus Service Bulletin A320–32– 1407, Revision 01, dated July 3, 2014; General Electric Service Bulletin 114122–32– 105, dated January 17, 2013; or General Electric Service Bulletin 114122–32–105, Revision 1, dated March 26, 2013; or General Electric Service Bulletin 114122–32–105, Revision 2, dated June 24, 2014); is not affected by the requirements of paragraphs (j) through (v) of this AD, provided that no MLG door actuator with a part number in figure 3 to paragraph (v) of this AD has been installed on that airplane since first flight, or since modification, as applicable. (2) An airplane in the configuration specified in paragraph (y)(1) of this AD, and with flight warning computers having P/N 350E053021212 (H2F7) installed (Airbus Modification 153741 applied in production, or modified in service as specified in Airbus Service Bulletin A320–31–1414), is not affected by the requirement of paragraph (t) of this AD and, following modification, Airbus A318/A319/A320/A321 TR TR437, L/ G GEAR NOT DOWNLOCKED, Issue 1.0, dated May 23, 2014 (if inserted), may be removed from the AFM of that airplane. (z) New Parts Installation Prohibitions (1) Except as specified in paragraph (z)(2) of this AD, as of the effective date of this AD, do not install on any airplane a MLG door actuator having a part number listed in figure 3 to paragraph (v) of this AD. (2) For an airplane subject to the requirements of paragraphs (u) and (v) of this AD, as applicable, do not install a MLG door actuator having a part number listed in figure 3 to paragraph (v) of this AD after modification of the airplane. (3) Except as specified in paragraph (z)(4) of this AD, as of the effective date of this AD, do not install on any airplane a flight warning computer (FWC) having a part number listed in figure 4 to paragraph (z) of this AD. (4) For an airplane subject to the requirements of paragraphs (u) and (v) of this AD, as applicable, do not install a FWC having a part number listed in figure 4 to paragraph (z) of this AD after modification of the airplane. FIGURE 4 TO PARAGRAPH (Z) OF THIS AD—AFFECTED PART NUMBERS Component name Part number Lhorne on DSK5TPTVN1PROD with PROPOSALS Flight warning computer .............................................................................................................................................. (aa) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before April 27, 2007 (the effective date of AD 2007–06– 18), using Airbus Service Bulletin A320–32– 1309, dated March 7, 2006. This service information is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraphs (k), (l), and (m) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–32–1390, Revision 01, dated September 21, 2011; or Revision 02, dated October 23, 2013. Airbus Service Bulletin A320–32–1390, Revision 01, dated September 21, 2011, was incorporated by reference in AD 2011–13–11. Airbus Service Bulletin A320–32–1390, Revision 02, dated October 23, 2013, is not incorporated by reference in this AD. (3) This paragraph provides credit for actions required by paragraphs (u) and (v) of VerDate Sep<11>2014 14:51 Sep 21, 2015 Jkt 235001 this AD, if those actions were performed before the effective date of this AD using General Electric Service Bulletin 114122–32– 105, dated January 17, 2013; or General Electric Service Bulletin 114122–32–105, Revision 1, dated March 26, 2013. This service information is not incorporated by reference in this AD. (bb) 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, PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 350E016187171 (C5) 350E017238484 (H1D1) 350E017248685 (H1D2) 350E017251414 (H1E1) 350E017271616 (H1E2) 350E018291818 (H1E3CJ) 350E018301919 (H1E3P) 350E018312020 (H1E3Q) 350E053020202 (H2E2) 350E053020303 (H2E3) 350E053020404 (H2E4) 350E053020606 (H2F2) 350E053020707 (H2F3) 350E053021010 (H2F3P) 350E053020808 (H2F4) 350E053020909 (H2F5) 350E053021111 (H2F6) 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-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) Required for Compliance (RC): If any Airbus 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 E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 80, No. 183 / Tuesday, September 22, 2015 / Proposed Rules 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 require approval of an AMOC. (3) Contacting the Manufacturer: As of the effective date of this AD, except as specified in paragraph (j) of this AD for the use of an alternative method to check the PFR for CFDS messages, 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (4) Previously Approved AMOCs: AMOCs approved previously for the AD 2011–13–11 and AD 2013–16–09 are approved as AMOCs for the corresponding provisions of this AD. (cc) Special Flight Permits Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified (if the operator elects to do so), provided the MLG remains extended and locked, and that no MLG recycle is done. (dd) Related Information Lhorne on DSK5TPTVN1PROD with PROPOSALS (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0221, dated September 30, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-0529-0003. (2) For Airbus 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. (3) For General Electric service information identified in this AD, contact GE Aviation, Customer Support Center, 1 Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: cs.techpubs@ge.com; Internet: http:// www.geaviation.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. Issued in Renton, Washington, on August 21, 2015. Kevin Hull, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–21730 Filed 9–21–15; 8:45 am] COMMODITY FUTURES TRADING COMMISSION 17 CFR Part 23 RIN 3038–AE17 Proposal To Amend the Definition of ‘‘Material Terms’’ for Purposes of Swap Portfolio Reconciliation Commodity Futures Trading Commission. ACTION: Notice of proposed rulemaking. AGENCY: The Commodity Futures Trading Commission (‘‘Commission’’ or ‘‘CFTC’’) proposes to amend a provision of the Commission’s regulations in connection with the material terms for which counterparties must resolve discrepancies when engaging in portfolio reconciliation. DATES: Comments must be received on or before November 23, 2015. ADDRESSES: You may submit comments, identified by RIN 3038–AE17, and Proposal to Amend the Definition of ‘‘Material Terms’’ for Purposes of Swap Portfolio Reconciliation by any of the following methods: • The agency’s Web site, at http:// comments.cftc.gov. Follow the instructions for submitting comments through the Web site. • Mail: Christopher Kirkpatrick, Secretary of the Commission, Commodity Futures Trading Commission, Three Lafayette Centre, 1155 21st Street NW., Washington, DC 20581. • Hand Delivery/Courier: Same as Mail above. • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments. Please submit your comments using only one method. All comments must be submitted in English, or if not, accompanied by an English translation. Comments will be posted as received to http:// www.cftc.gov. You should submit only information that you wish to make available publicly. If you wish the Commission to consider information that you believe is exempt from disclosure under the Freedom of Information Act, a petition for confidential treatment of the exempt information may be submitted according to the procedures established in § 145.9 of the Commission’s regulations.1 The Commission reserves the right, but shall have no obligation, to review, pre-screen, filter, redact, refuse or remove any or all of your submission SUMMARY: BILLING CODE 4910–13–P 1 17 CFR 145.9. Commission regulations referred to herein are found at 17 CFR Chapter I. VerDate Sep<11>2014 14:51 Sep 21, 2015 Jkt 235001 PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 57129 from http://www.cftc.gov that it may deem to be inappropriate for publication, such as obscene language. All submissions that have been redacted or removed that contain comments on the merits of the rulemaking will be retained in the public comment file and will be considered as required under the Administrative Procedure Act and other applicable laws, and may be accessible under the Freedom of Information Act. FOR FURTHER INFORMATION CONTACT: Frank N. Fisanich, Chief Counsel, 202– 418–5949, ffisanich@cftc.gov; Katherine S. Driscoll, Associate Chief Counsel, 202–418–5544, kdriscoll@cftc.gov; Gregory Scopino, Special Counsel, 202– 418–5175, gscopino@cftc.gov, Division of Swap Dealer and Intermediary Oversight, Commodity Futures Trading Commission, Three Lafayette Centre, 1155 21st Street NW., Washington, DC 20581. SUPPLEMENTARY INFORMATION: I. Background On September 11, 2012, the Commission published in the Federal Register final rules § 23.500 through § 23.505 2 establishing requirements for the timely and accurate confirmation of swaps, the reconciliation and compression of swap portfolios, and documentation of swap trading relationships between swap dealers (‘‘SDs’’),3 major swap participants (‘‘MSPs’’),4 and their counterparties. These regulations were promulgated by the Commission pursuant to the authority granted under Sections 4s(h)(1)(D), 4s(h)(3)(D), and 4s(i) of the Commodity Exchange Act (the ‘‘CEA’’),5 2 Confirmation, Portfolio Reconciliation, Portfolio Compression, and Swap Trading Relationship Documentation Requirements for Swap Dealers and Major Swap Participants, 77 FR 55904 (Sept. 11, 2012) (hereinafter, ‘‘Portfolio Reconciliation Final Rule’’). 3 Generally, an SD is any person who, in addition to transacting in a notional amount of swaps in excess of specified de minimis thresholds, holds itself out as a dealer in swaps, makes a market in swaps, regularly enters into swaps with counterparties as an ordinary course of business for its own account, or engages in any activity causing it to be commonly known in the trade as a dealer or market maker in swaps. See 7 U.S.C. 1a(49); 17 CFR 1.3(ggg). 4 Generally, an MSP is any non-dealer that maintains a substantial position in swaps for any of the specified major swap categories, whose outstanding swaps create substantial counterparty exposure that could have serious adverse effects on the financial stability of the United States banking system or financial markets, or any financial entity that is highly leveraged relative to the amount of capital such entity holds and that is not subject to capital requirements established by an appropriate Federal banking agency and maintains a substantial position in outstanding swaps in any major swap category. See 7 U.S.C. 1a(33); 17 CFR 1.3(hhh). 5 7 U.S.C. 6s(h)(1)(D), 6s(h)(3)(D) and 6s(i). E:\FR\FM\22SEP1.SGM 22SEP1

Agencies

[Federal Register Volume 80, Number 183 (Tuesday, September 22, 2015)]
[Proposed Rules]
[Pages 57122-57129]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21730]



[[Page 57122]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0529; Directorate Identifier 2013-NM-260-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.

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SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. 
The NPRM proposed to supersede Airworthiness Directives (AD) 2011-13-11 
and AD 2013-16-09. AD 2011-13-11 currently requires an amendment of the 
airplane flight manual (AFM), repetitive checks of specific centralized 
fault display system (CFDS) messages, an inspection of the opening 
sequence of the main landing gear (MLG) door actuator for discrepancies 
if certain messages are found, and corrective actions if necessary. AD 
2013-16-09 currently requires an inspection to determine airplane 
configuration and part numbers of the landing gear control interface 
unit and MLG door actuators; and, for affected airplanes, repetitive 
inspections of the opening sequence of the MLG door actuator, and 
replacement of the MLG door actuator if necessary; and provides 
optional terminating action for the repetitive inspections. The NPRM 
was prompted by a determination that the interval of the MLG door 
opening sequence inspection must be reduced. The NPRM proposed to 
reduce the interval of the MLG door opening sequence inspection, and 
also to replace or modify certain MLG door actuators. This action 
revises the NPRM by adding a flushing procedure to be performed when 
installing a new MLG door actuator. We are proposing this supplemental 
NPRM (SNPRM) to detect and correct deterioration of the damping ring 
and associated retaining ring of the MLG door actuator, which can 
sufficiently increase the friction inside the actuator to restrict 
opening of the MLG door by gravity, during operation of the landing 
gear alternate (free-fall) extension system. This condition could 
prevent the full extension and/or down-locking of the MLG, possibly 
resulting in MLG collapse during landing and consequent damage to the 
airplane and injury to occupants. 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 November 6, 2015.

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 Airbus service information identified in this proposed 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. For General Electric service information 
identified in this AD contact GE Aviation, Customer Support Center, 1 
Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; email: 
cs.techpubs@ge.com; Internet: http://www.geaviation.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-
0529; 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.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0529; 
Directorate Identifier 2013-NM-260-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 A318, 
A319, A320, and A321 series airplanes. The NPRM published in the 
Federal Register on August 13, 2014 (79 FR 47395; corrected August 27, 
2014 (79 FR 51117)) (``the NPRM''). The NPRM proposed to supersede AD 
2011-13-11, Amendment 39-16734 (76 FR 37241, June 27, 2011) (``AD 2011-
13-11''); and AD 2013-16-09, Amendment 39-17547 (78 FR 48286, August 8, 
2013) (``AD 2013-16-09''). AD 2011-13-11 currently requires an 
amendment of the AFM, repetitive checks of specific CFDS messages, an 
inspection of the opening sequence of the MLG door actuator for 
discrepancies if certain messages are found, and corrective actions if 
necessary. AD 2013-16-09 currently requires an inspection to determine 
airplane configuration and part numbers of the landing gear control 
interface unit and MLG door actuators; and, for affected airplanes, 
repetitive inspections of the opening sequence of the MLG door 
actuator, and replacement of the MLG door actuator if necessary; and 
provides optional terminating action for the repetitive inspections. 
The NPRM was prompted by a determination that the interval of the MLG 
door opening sequence inspection must be reduced. The NPRM proposed to 
reduce the interval of the MLG door opening

[[Page 57123]]

sequence inspection, and also to replace or modify certain MLG door 
actuators.

Actions Since Previous NPRM Was Issued

    Since we issued the NPRM, we have determined that a flushing 
procedure must be performed when installing a new MLG door actuator. 
The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0221, dated September 30, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A318, 
A319, A320, and A321 series airplanes. The MCAI states:

    Some operators reported slow operation of the main landing gear 
(MLG) door opening/closing sequence, leading to the generation of 
[electronic centralized aircraft monitor] ECAM warnings during the 
landing gear retraction or extension sequence.
    Investigations showed that the damping ring and associated 
retaining ring of the MLG door actuator may deteriorate. The 
resultant debris increases the friction inside the actuator which 
can be sufficiently high to restrict opening of the MLG door by 
gravity, during operation of the landing gear alternate (freefall) 
extension system.
    This condition, if not corrected, could prevent the full 
extension and/or down locking of the MLG, possibly resulting in MLG 
collapse during landing or rollout and consequent damage to the 
aeroplane and injury to occupants.
    [An EASA AD] was issued [and later revised] to require 
repetitive inspections of the opening sequence of the MLG door in 
order to identify the affected actuators, and to introduce as an 
optional terminating action Airbus production Modification (mod) 
38274 and associated [Airbus] Service Bulletin (SB) A320-32-1338, 
which incorporate an improved retaining ring, located on the piston 
rod's extension end, and a new piston rod with machined shoulder to 
accommodate the thicker section of the modified retaining ring.
    After in-service introduction of the new MLG door actuator, Part 
Number (P/N) 114122012 (Post-mod 38274--SB A320-32-1338), several 
operators reported failures of internal parts of the MLG door 
actuator. Investigations confirmed that these failures could result 
in slow extension of the actuator rod, delaying the MLG door 
operation, or possibly stopping just before the end of the stroke, 
preventing the door to reach the fully open position.
    [An EASA AD], which superseded EASA AD 2006-0112R1 [http://ad.easa.europa.eu/blob/easa_ad_2006_0112_R1_superseded.pdf/AD_2006-0112R1_1], was issued [and later revised] to require amendment of 
the applicable Airplane Flight Manual (AFM), repetitive checks of 
specific Centralized Fault Display System (CFDS) messages, 
repetitive inspections of the opening sequence of the MLG door 
actuator and, depending on findings, corrective action(s).
    Since EASA AD 2011-0069R1 [http://ad.easa.europa.eu/blob/easa_ad_2011_0069_R1_superseded.pdf/AD_2011-0069R1_1] was issued, 
Airbus introduced a reinforced MLG door actuator P/N 114122014 (mod 
153655). Airbus issued SB A320-32-1407 containing instructions for 
in-service replacement of the affected MLG door actuators, or 
modification of the actuators to the new standard.
    In addition, following a recent occurrence with a gear extension 
problem, the result of additional analyses by Airbus revealed that 
the CFDS expected specific messages may not be generated and as a 
result, repetitive checks of messages are not effective for 
aeroplanes fitted with landing gear control interface unit (LGCIU) 
interlink communication ARINC 429 (applied in production through 
Airbus mod 39303, or in service through Airbus SB A320-32-1409), in 
combination with LGCIUs 80-178-02-88012 or 80-178-03-88013 in both 
positions and at least one MLG door actuator pre-mod 153655 (pre-
Airbus SB A320-32-1407--pre-GE SB 114122-32-105) installed.
    Prompted by these findings, EASA issued Emergency AD 2013-0132-E 
[http://ad.easa.europa.eu/blob/easa_ad_2013_0132_E_superseded.pdf/EAD_2013-0132-E_1 (which corresponds to FAA AD 2013-16-09)] to 
require identification of the affected aeroplanes to establish the 
configuration and, for those aeroplanes, repetitive inspections of 
the opening sequence of the MLG door actuator and, depending on 
findings, replacement of the MLG door actuator. That [EASA] AD also 
provided an optional terminating action by disconnection of the 
interlink for certain LGCIUs, or in-service modification of the 
aeroplane through Airbus SB A320-32-1407 (equivalent to Airbus 
production mod 153655).
    Since those ADs (EASA AD 2011-0069R1 and EASA AD 2013-0132-E) 
were issued, analyses performed by Airbus have revealed that the MLG 
door opening sequence inspection interval needed to be reduced, and 
that the (previously optional) terminating action needed to be made 
mandatory.
    Prompted by these findings, EASA issued AD 2013-0288 [http://ad.easa.europa.eu/blob/easa_ad_2013_0288_superseded.pdf/AD_2013-0288_1], retaining the requirements of EASA AD 2011-0069R1 and EASA 
AD 2013-0132-E, which were superseded, but with reduced inspection 
intervals, and to require replacement or modification, as 
applicable, of the affected MLG door actuators as terminating action 
to the monitoring and repetitive checks and inspections.
    Following introduction of post-mod 153655 MLG door actuators on 
in-service aeroplanes, it has been observed that, in case the 
removed pre-mod MLG door actuator has internal damage, contamination 
of the hydraulic system could have occurred.
    This condition, if not detected and corrected, could result in 
performance degradation (damping degradation) of the post-mod MLG 
door actuator. Testing performed with a new actuator tested in 
heavily contaminated hydraulic system did not show abnormal 
hydraulic Restriction/blockage. It is thus not requested to perform 
this ``flushing procedure'' on aircraft already retrofitted with 
std-14 actuators.
    In addition, since EASA AD 2013-0288 was issued, the applicable 
AFM was revised and repetitive checks of specific CFDS messages are 
no longer considered to be required, due to the reduced intervals 
required by EASA AD 2013-0288.
    For the reasons described above, this [EASA] AD partially 
retains the requirements of EASA AD 2013-0288, which is superseded, 
introduces improved wording for clarification and requires, in 
addition to the revised operational (AFM) procedure, hydraulic 
flushing prior to any installation of a post-mod MLG door actuator.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-529-0003.

Related Service Information Under 1 CFR part 51

    Airbus has issued Service Bulletins A320-32-1390, Revision 03, 
dated July 3, 2014; and A320-32-1407, Revision 01, dated July 3, 2014. 
Airbus has also issued A318/A319/A320/A321 Temporary Revision (TR) 
TR437, L/G GEAR NOT DOWNLOCKED, Issue 1.0, dated May 23, 2014, to the 
Airplane Flight Manual (AFM).
    Airbus Service Bulletin A320-32-1390, Revision 03, dated July 3, 
2014, describes procedures for inspecting the operation of the MLG door 
opening sequence to determine if an actuator is defective, flushing 
contamination from the landing gear extension and retraction system 
(LGERS), and replacing the door actuator if necessary.
    Airbus Service Bulletin A320-32-1407, Revision 01, dated July 3, 
2014, describes procedures for flushing contamination from the LGERS, 
and installing new MLG door actuators.
    Airbus A318/A319/A320/A321 TR TR437, L/G GEAR NOT DOWNLOCKED, Issue 
1.0, dated May 23, 2014, to the AFM updates the procedure used for 
incomplete landing gear extension during approach.
    General Electric Service Bulletin 114122-32-105, Revision 2, dated 
June 24, 2014, describes procedures for conversion of a MLG door 
actuator and to remove unwanted material from the hydraulic fluid 
route.
    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 
SNPRM.

[[Page 57124]]

Comments

    We gave the public the opportunity to participate in developing 
this SNPRM. We considered the comments received.

Requests To Adopt the Actions of EASA Airworthiness Directive 2014-
0221, Dated September 30, 2014, and Certain Service Bulletins

    Airbus requested that we revise the NPRM to adopt the requirements 
of EASA Airworthiness Directive 2014-0221, dated September 30, 2014; 
Airbus Service Bulletin A320-32-1390, Revision 03, dated July 3, 2014; 
and Airbus Service Bulletin A320-32-1407 Revision 01, dated July 3, 
2014. Airbus stated that EASA issued a global airplane flight manual 
(AFM) TR to mandate updated operational procedures. US Airways 
requested that we reference Airbus Service Bulletin A320-32-1407, 
Revision 01, dated July 3, 2014, and a new AFM procedure referenced in 
``FOT 999-0032/14.''
    We agree with the commenters' requests. EASA Airworthiness 
Directive 2014-0221, dated September 30, 2014, requires, among other 
things, a revised operational AFM procedure, and hydraulic flushing 
prior to any installation of a post-modification MLG door actuator. We 
have revised paragraphs (j), (k), (l), (m), and (w) as designated in 
the NPRM (paragraphs (j), (k), (l), (m), and (x) in this SNPRM)) to 
reference Airbus Service Bulletin A320-32-1390, Revision 03, dated July 
3, 2014; and paragraphs (r), (t), (u), (w), and (x) as designated in 
the NPRM (paragraphs (r), (u), (v), (x), and (y) in this SNPRM)) to 
reference Airbus Service Bulletin A320-32-1407, Revision 01, dated July 
3, 2014; as the appropriate sources of service information for 
accomplishing the proposed actions.

Request To Not Mandate the Actions in Airbus Service Bulletin A320-32-
1407, Revision 01, Dated July 3, 2014

    United Airlines requested that we not require the actions in Airbus 
Service Bulletin A320-32-1407, Revision 01, dated July 3, 2014. United 
Airlines stated that Airbus Service Bulletin A320-32-1407, Revision 01, 
dated July 3, 2014, recommends that operators flush the affected 
hydraulic system. United Airlines stated that it disagrees with this 
proposed action and explained that Airbus instituted this requirement 
to flush the hydraulic system as it failed to recommend the removal, 
inspection, and cleaning of the restrictors during the modification of 
the MLG door actuator to the part number (P/N) 114122014 configuration. 
United Airlines also stated that it has opted to overhaul the MLG door 
actuators as well as perform the modification described in Airbus 
Service Bulletin A320-32-1407, dated May 14, 2013. United Airlines 
explained that this overhaul requires that the restrictors (P/N 
114122233 and P/N 114122232) and transfer pipe be removed, inspected, 
and cleaned. United Airlines stated that it is of the opinion that 
flushing the hydraulic system is not required as there is no 
contamination present in the restrictors or the transfer pipe.
    We disagree with the commenter's request. Airbus informed the FAA 
that debris can leave the damaged actuator and remain in the hydraulic 
lines connected to the door actuator. Flushing of the hydraulic system 
is required to prevent debris from entering the new actuator. If debris 
enters the new actuator, its performance can be affected. The flow rate 
during normal operation is insufficient to ensure complete flushing of 
the debris to the hydraulic low pressure filter within a few door 
cycles. Therefore, a specific maintenance procedure has been defined 
and introduced in Airbus Service Bulletin A320-32-1407, Revision 01, 
dated July 3, 2014; and General Electric Service Bulletin 114122-32-
105, Revision 2, dated June 24, 2014. EASA has issued AD 2014-0221, 
dated September 30, 2014, requiring flushing of the affected hydraulic 
system in accordance with Airbus Service Bulletin A320-32-1407, 
Revision 01, dated July 3, 2014.

Request To Provide Credit for Previous Actions

    US Airways requested that we provide credit for the actions 
required by paragraphs (t) and (u) of the proposed AD (paragraphs (u) 
and (v) of this SNPRM)), if those actions were done before the 
effective date of the AD using Airbus Service Bulletins A320-32-1407, 
dated May 14, 2013, or Revision 01, dated July 3, 2014; or General 
Electric Service Bulletin 114122-32-105, dated January 17, 2013.
    We partially agree with the commenter's request. In this SNPRM, 
paragraph (aa) already provides credit for General Electric Service 
Bulletin 114122-32-105, dated January 17, 2013, for the actions in 
paragraphs (u) and (v) done prior to the effective date of the final 
rule. We do not agree with giving credit for Airbus Service Bulletin 
A320-32-1407, dated May 14, 2013; or Revision 01, dated July 3, 2014; 
because those service bulletins do not require flushing the hydraulic 
system prior to the installation of P/N 114122014. We have not changed 
the proposed AD in this regard.

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 NPRM. 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 ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives 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 Required for Compliance (RC) 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 Airbus service information, procedures and tests identified 
as RC 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

[[Page 57125]]

identified as RC will require approval of an AMOC.

Changes to the Proposed AD

    This SNPRM makes the following changes to the NPRM.
    We have moved the credit for Airbus Service Bulletin A320-32-1309, 
dated March 7, 2006, specified in paragraph (g) of AD 2011-13-11, into 
paragraph (aa)(1) of the proposed AD.
    We have reformatted and redesignated three tables as figures to 
comply with requirements of the Office of the Federal Register, as 
follows:
     ``Table 1 to Paragraph (p) of this AD--Affected Part 
Numbers'' is ``Figure 2 to Paragraph (p) of this AD--Affected Part 
Numbers;''
     ``Table 2 to Paragraph (v) of this AD--Affected Part 
Numbers'' is ``Figure 3 to Paragraph (v) of this AD--Affected Part 
Numbers;'' and
     ``Table 3 to Paragraph (z) of this AD--Affected Part 
Numbers'' is ``Figure 4 to Paragraph (z) of this AD.''

Costs of Compliance

    We estimate that this SNPRM affects 953 airplanes of U.S. registry.
    The actions that are required by AD 2011-13-11, and retained in 
this SNPRM, take about 7 work-hours per product, per inspection cycle, 
at an average labor rate of $85 per work-hour. Based on these figures, 
the estimated cost of the actions that are required by AD 2011-13-11 is 
$595 per product.
    The actions that are required by AD 2013-16-09, and retained in 
this SNPRM, take about 3 work-hours per product, per inspection cycle, 
at an average labor rate of $85 per work-hour. Based on these figures, 
the estimated cost of the actions that were required by AD 2013-16-09 
is $255 per product.
    We also estimate that it would take about 19 work-hours per product 
to comply with the basic requirements of this SNPRM. The average labor 
rate is $85 per work-hour. Required parts would cost about $17,140 per 
product. Based on these figures, we estimate the cost of this SNPRM on 
U.S. operators to be $17,873,515, or $18,755 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 3 work-hours, for a cost of $255 per product. We have no way 
of determining the number of aircraft that might need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directives (AD) 2011-13-11, Amendment 39-
16734 (76 FR 37241, June 27, 2011) (``AD 2011-13-11''); and AD 2013-16-
09, Amendment 39-17547 (78 FR 48286, August 8, 2013) (``AD 2013-16-
09''); and
0
b. Adding the following new AD:

Airbus: Docket No. FAA-2014-0529; Directorate Identifier 2013-NM-
260-AD.

(a) Comments Due Date

    We must receive comments by November 6, 2015.

(b) Affected ADs

    This AD replaces AD 2011-13-11, Amendment 39-16734 (76 FR 37241, 
June 27, 2011) (``AD 2011-13-11''); and AD 2013-16-09, Amendment 39-
17547 (78 FR 48286, August 8, 2013) (``AD 2013-16-09'').

(c) Applicability

    This AD applies to the Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), (c)(3), and 
(c)(4) of this AD, all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
Gear.

(e) Reason

    This AD was prompted by a determination that the inspection 
interval of the main landing gear (MLG) door opening sequence must 
be reduced. We are issuing this AD to detect and correct 
deterioration of the damping ring and associated retaining ring of 
the MLG door actuator, which can sufficiently increase the friction 
inside the actuator to restrict opening of the MLG door by gravity, 
during operation of the landing gear alternate (free-fall) extension 
system. This condition could prevent the full extension and/or down-
locking of the MLG, possibly resulting in MLG collapse during 
landing and consequent damage to the aeroplane and injury to 
occupants.

(f) Compliance

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

(g) Retained Repetitive Inspections/Replacement, With a Formatting 
Change

    This paragraph restates the requirements of paragraph (g) of AD 
2011-13-11, with a formatting change. At the time specified in 
paragraph (g)(1) or (g)(2) of this AD, as applicable: Do a general 
visual inspection of the operation of the MLG door opening sequence 
to determine if a defective actuator is installed by doing all the 
applicable actions, including replacing the door actuator, as 
applicable, specified in the Accomplishment Instructions of Airbus 
Service Bulletin A320-32-1309, Revision 01, dated June 19, 2006. Do 
all applicable replacements before further flight. Repeat the 
inspection thereafter at intervals not to exceed 900 flight cycles. 
Doing the

[[Page 57126]]

inspection required by paragraph (l) of this AD terminates the 
requirements of this paragraph.
    (1) For airplanes on which a record of the total number of 
flight cycles on the MLG door actuator is available: Before the 
accumulation of 3,000 total flight cycles on the MLG door actuator, 
or within 800 flight cycles after April 27, 2007 (the effective date 
of AD 2007-06-18, Amendment 39-14999 (72 FR 13681, March 23, 2007)), 
whichever is later.
    (2) For airplanes on which a record of the total number of 
flight cycles on the MLG door actuator is not available: Within 800 
flight cycles after April 27, 2007 (the effective date of AD 2007-
06-18).
    (3) For the purposes of this AD, a general visual inspection is: 
``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
enhance visual access to all exposed surfaces in the inspection 
area. This level of inspection is made under normally available 
lighting conditions such as daylight, hangar lighting, flashlight, 
or droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

(h) Retained Provision Regarding Reporting/Parts Return, With No 
Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2011-13-11, with no changes. Although the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1309, Revision 01, 
dated June 19, 2006, specify submitting certain information to the 
manufacturer and sending defective actuators back to the component 
manufacturer for investigation, this AD does not include those 
requirements.

(i) Retained Revision of the Airplane Flight Manual (AFM), With 
Formatting Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2011-13-11, with formatting changes. Within 14 days after July 12, 
2011 (the effective date of AD 2011-13-11), revise the Emergency 
Procedure Section of the AFM to incorporate the information in 
figure 1 to paragraph (i) of this AD. This may be done by inserting 
a copy of this AD into the AFM. When a statement identical to that 
in figure 1 to paragraph (i) of this AD has been included in the 
Emergency Procedure Section of the general revisions of the AFM, the 
general revisions may be inserted into the AFM, and the copy of this 
AD may be removed from the AFM. Doing the actions required by 
paragraph (t) of this AD terminates the requirements of this 
paragraph.

           Figure 1 to Paragraph (i) of This AD--AFM Revision
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
 If ECAM triggers the ``L/G GEAR NOT DOWNLOCKED'' warning, apply
 the following procedure:
Recycle landing gear.
 If unsuccessful after 2 min:
Extend landing gear by gravity. Refer to ABN-32 L/G GRAVITY EXTENSION.
------------------------------------------------------------------------

(j) Retained Repetitive Checks, With New Optional Actions and New 
Service Information

    This paragraph restates the requirements of paragraph (j) of AD 
2011-13-11, with new optional actions and new service information. 
Within 14 days after July 12, 2011 (the effective date of AD 2011-
13-11), or before the accumulation of 800 total flight cycles, 
whichever occurs later, check the post flight report (PFR) for 
centralized fault display system (CFDS) messages triggered within 
the last 8 days, in accordance with paragraph 4.2.1 of Airbus All 
Operators Telex (AOT) A320-32A1390, dated February 10, 2011. Repeat 
the check thereafter at intervals not to exceed 8 days or 5 flight 
cycles, whichever occurs later. If done in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, the use of an alternative method to check 
the PFR for CFDS messages (e.g., AIRMAN) is acceptable in lieu of 
this check if the messages can be conclusively determined from that 
method. Repetitive inspections of the door opening sequence of the 
left-hand (LH) and right-hand (RH) doors of the MLG, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-32-1390, Revision 03, dated July 13, 2014, are an acceptable 
method of compliance for the actions required by this paragraph. 
Repetitive inspections of the door opening sequence of the LH and RH 
doors of the MLG of an airplane, as required by paragraph (p) of 
this AD, is an acceptable method to comply with the requirements of 
this paragraph.

(k) Retained On-Condition Inspection, With New Service Information

    This paragraph restates the requirements of paragraph (k) of AD 
2011-13-11, with new service information. If, during any check 
required by paragraph (j) of this AD, a pair of specific CFDS 
messages specified in paragraph 4.2.1 of Airbus AOT A320-32A1390, 
dated February 10, 2011, has been triggered by both landing gear 
control and indication units (LGCIU) for the same flight, before 
further flight, inspect the door opening sequence of the affected 
doors of the MLG for discrepancies (i.e., if any condition specified 
in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT A320-
32A1390, dated February 10, 2011, is not met; or if any door 
actuator fails any inspection check specified in Airbus Service 
Bulletin A320-32-1390, Revision 03, dated July 13, 2014). Do the 
inspection in accordance with paragraph 4.2.2 of Airbus AOT A320-
32A1390, dated February 10, 2011; or the Accomplishment Instructions 
of Airbus Service Bulletin A320-32-1390, Revision 03, dated July 13, 
2014. As of the effective date of this AD, use only Airbus Service 
Bulletin A320-32-1390, Revision 03, dated July 13, 2014, for the 
actions required by this paragraph.

(l) Retained Repetitive Inspections, With New Service Information, New 
Optional Actions, and Reduced Compliance Times

    This paragraph restates the requirements of paragraph (l) of AD 
2011-13-11, with new service information, new optional actions, and 
reduced compliance times. At the applicable time specified in 
paragraph (l)(1) or (l)(2) of this AD: Inspect the door opening 
sequence of the LH and RH doors of the MLG for discrepancies (i.e., 
if any condition specified in steps (a) through (d) of paragraph 
4.2.2 of Airbus AOT A320-32A1390, dated February 10, 2011, is not 
met; or if any door actuator fails any inspection check specified in 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1390, Revision 03, dated July 13, 2014). Do the inspection in 
accordance with the instructions of paragraph 4.2.2 of Airbus AOT 
A320-32A1390, dated February 10, 2011; or the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1390, Revision 03, 
dated July 13, 2014. As of the effective date of this AD, use only 
Airbus Service Bulletin A320-32-1390, Revision 03, dated July 13, 
2014, for the actions required by this paragraph. Repeat the 
inspection within 8 days or 5 flight cycles after the effective date 
of this AD, whichever occurs later, without exceeding 425 flight 
cycles since the most recent inspection; and thereafter repeat the 
inspection at intervals not to exceed 8 days or 5 flight cycles, 
whichever occurs later. In addition, whenever any airplane is not 
operated for a period longer than 8 days, do the inspection before 
further flight. Doing this inspection terminates the requirements of 
paragraph (g) of this AD. Repetitive inspections of the door opening 
sequence of the LH and RH doors of the MLG of an airplane, as 
required by paragraph (p) of this AD, is an acceptable method to 
comply with the requirements of this paragraph.
    (1) For airplanes on which an inspection required by paragraph 
(g) of this AD has been done as of July 12, 2011 (the effective date 
of AD 2011-13-11): Within 800 flight cycles after doing the most 
recent inspection required by paragraph (g) of this AD, or within 
100 flight cycles after July 12, 2011, whichever occurs later.
    (2) For airplanes on which an inspection required by paragraph 
(g) of this AD has not been done as of July 12, 2011 (the effective 
date of AD 2011-13-11): Within 800 flight cycles after July 12, 
2011.

(m) Retained Replacement, With New Service Information

    This paragraph restates the requirements of paragraph (m) of AD 
2011-13-11, with new

[[Page 57127]]

service information. If any discrepancy (i.e., if any condition 
specified in steps (a) through (d) of paragraph 4.2.2 of Airbus AOT 
A320-32A1390, dated February 10, 2011, is not met; or if any door 
actuator fails any inspection check specified in the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1390, Revision 03, 
dated July 13, 2014) is found during any inspection required by 
paragraph (k) or (l) of this AD, before further flight, replace the 
affected MLG door actuator with a new MLG door actuator, in 
accordance with the instructions of Airbus AOT A320-32A1390, dated 
February 10, 2011; or Airbus Service Bulletin A320-32-1390, Revision 
03, dated July 13, 2014. As of the effective date of this AD, use 
only Airbus Service Bulletin A320-32-1390, Revision 03, dated July 
13, 2014, to do the actions required by this paragraph.

(n) Retained Statement of No Terminating Action for Certain 
Requirements, With No Changes

    This paragraph restates the statement of paragraph (n) of AD 
2011-13-11, with no changes. Replacement of the MLG door actuator as 
required by paragraph (m) of this AD is not a terminating action for 
the repetitive actions required by paragraphs (j) and (l) of this 
AD.

(o) Retained Configuration and Part Number Determination, With No 
Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2013-16-09, with no changes. At the later of the compliance times 
specified in paragraphs (o)(1) and (o)(2) of this AD: Do an 
inspection to determine the configuration (modification status) of 
the airplane and identify the part number of the LH and RH LGCIU and 
MLG door actuators. A review of the airplane delivery or maintenance 
records is acceptable for compliance with the requirements of this 
paragraph provided the airplane configuration and installed 
components can be conclusively determined from that review.
    (1) Prior to the accumulation of 800 total flight cycles since 
first flight of the airplane.
    (2) Within 14 days after August 23, 2013 (the effective date of 
AD 2013-16-09).

(p) Retained MLG Door Opening Sequence Repetitive Inspections, With No 
Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2013-16-09, with no changes. If, during the determination and 
identification required by paragraph (o) of this AD, the 
configuration of the airplane is determined to be post-Airbus 
Modification 39303 or post-Airbus Service Bulletin A320-32-1409 
(Interlink Communication ARINC 429 installed), and both an LGCIU and 
a MLG door actuator are installed with a part number listed in 
figure 2 to paragraph (p) of this AD: Except as provided by 
paragraph (s) of this AD, at the later of the compliance times 
specified in paragraphs (o)(1) and (o)(2) of this AD, and thereafter 
at intervals not to exceed 8 days or 5 flight cycles, whichever 
occurs later, do an inspection of the door opening sequence of the 
LH and RH MLG doors, in accordance with the instructions of Airbus 
AOT A32N001-13, dated June 24, 2013.

       Figure 2 to Paragraph (p) of This AD--Affected Part Numbers
------------------------------------------------------------------------
                  Component name                         Part number
------------------------------------------------------------------------
LGCIU (LH and RH).................................       80-178-02-88012
                                                         80-178-03-88013
MLG door actuator.................................             114122006
                                                               114122007
                                                               114122009
                                                               114122010
                                                               114122011
                                                               114122012
------------------------------------------------------------------------

(q) Retained MLG Door Opening Sequence Corrective Action, With No 
Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2013-16-09, with no changes. If a slow door operation or restricted 
extension is found during any inspection required by paragraph (p) 
of this AD: Before further flight, replace the affected MLG door 
actuator with a new or serviceable actuator, in accordance with the 
instructions of Airbus AOT A32N001-13, dated June 24, 2013.

(r) Retained Terminating Action Limitation for Certain Actions, With 
New Service Information

    This paragraph restates the requirements of paragraph (j) of AD 
2013-16-09, with new service information. Replacement of a MLG door 
actuator, as required by paragraph (q) of this AD, does not 
constitute terminating action for the repetitive inspections 
required by paragraph (p) of this AD, unless MLG door actuators 
having P/N 114122014 are installed on both LH and RH sides, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1407, dated May 14, 2013; or Airbus Service 
Bulletin A320-32-1407, Revision 01, dated July 3, 2014. As of the 
effective date of this AD, use only Airbus Service Bulletin A320-32-
1407, Revision 01, dated July 3, 2014, for the actions required by 
this paragraph.

(s) Retained Repetitive Inspection Exception, With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2013-16-09, with no changes. Airplanes on which the LGCIU interlink 
is disconnected (Airbus Modification 155522 applied in production, 
or modified in-service in accordance with the instructions of Airbus 
AOT A32N001-13, dated June 24, 2013), or on which MLG door actuators 
having P/N 114122014 are installed on both LH and RH sides (Airbus 
Modification 153655 applied in production, or modified in-service as 
described in Airbus Service Bulletin A320-32-1407), are not required 
to do the actions required by paragraph (p) of this AD, provided 
that the airplane is not modified to a configuration as defined in 
paragraph (p) of this AD.

(t) New Revision of the AFM

    Within 14 days after the effective date of this AD, revise the 
Emergency Procedure Section of the AFM to incorporate Airbus A318/
A319/A320/A321 Temporary Revision (TR) TR437, L/G GEAR NOT 
DOWNLOCKED, Issue 1.0, dated May 23, 2014. When this TR has been 
included in general revisions of the AFM, the general revisions may 
be inserted in the AFM, provided the relevant information in the 
general revision is identical to that in this TR, and the copy of 
this TR may be removed from the AFM. Doing the action required by 
this paragraph terminates the actions required by paragraph (i) of 
this AD.

(u) New Replacement of MLG Door Actuator Having P/N 114122012

    Within 12 months after the effective date of this AD: Replace 
each MLG door actuator having P/N 114122012 with a MLG door actuator 
having P/N 14122014, and flush the affected hydraulic system, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1407, Revision 01, dated July 3, 2014; or modify 
each actuator, including doing all applicable related investigative 
and corrective actions, in accordance with the Accomplishment 
Instructions of General Electric Service Bulletin 114122-32-105, 
Revision 2, dated June 24, 2014; except where General Electric 
Service Bulletin 114122-32-105, Revision 2, dated June 24, 2014, 
specifies to contact the manufacturer, before further flight, repair 
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).

(v) New Replacement of Certain Other MLG Door Actuators

    Within 24 months after the effective date of this AD: Replace 
each MLG door actuator having a part number listed in figure 3 to 
paragraph (v) of this AD, except P/N 114122012, with a MLG door 
actuator having P/N 14122014, and flush the affected hydraulic 
system, in accordance with Accomplishment Instructions of Airbus 
Service Bulletin A320-32-1407, Revision 01, dated July 3, 2014; or 
modify each actuator, including doing all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of General Electric Service Bulletin 
114122-32-105, Revision 2, dated June 24, 2014; except where General 
Electric Service Bulletin 114122-32-105, Revision 2, dated June 24, 
2014, specifies to contact the manufacturer, before further flight, 
repair using a method approved by the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the EASA; or 
Airbus's EASA DOA.

       Figure 3 to Paragraph (v) of This AD--Affected Part Numbers
------------------------------------------------------------------------
                      Component name                         Part number
------------------------------------------------------------------------
MLG door actuator.........................................     114122006
                                                               114122007
                                                               114122009
                                                               114122010
                                                               114122011
                                                               114122012
------------------------------------------------------------------------

(w) New Terminating Action

    Modification of an airplane as required by paragraphs (u) and 
(v) of this AD, as applicable, constitutes terminating action for

[[Page 57128]]

all repetitive actions (PFR monitoring checks and inspections) 
required by this AD for that airplane.

(x) New Conditional Terminating Action

    Replacement of a MLG door actuator as required by paragraphs (m) 
and (q) of this AD; or corrective actions as specified in Airbus AOT 
A320-32A1390, dated February 10, 2011; or replacement of a MLG door 
actuator as specified in Airbus Service Bulletin A320-32-1390, 
Revision 03, dated July 13, 2014; does not constitute terminating 
action for the repetitive inspections required by paragraphs (j), 
(l), and (p) of this AD, unless MLG door actuators having P/N 
114122014 are installed on both LH and RH sides, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1407, Revision 01, dated July 3, 2014.

(y) New Exception to AD Requirements

    (1) An airplane on which MLG door actuators having P/N 114122014 
are installed on both LH and RH sides (Airbus Modification 153655 
applied in production, or modified in service as specified in Airbus 
Service Bulletin A320-32-1407, dated May 14, 2013; Airbus Service 
Bulletin A320-32-1407, Revision 01, dated July 3, 2014; General 
Electric Service Bulletin 114122-32-105, dated January 17, 2013; or 
General Electric Service Bulletin 114122-32-105, Revision 1, dated 
March 26, 2013; or General Electric Service Bulletin 114122-32-105, 
Revision 2, dated June 24, 2014); is not affected by the 
requirements of paragraphs (j) through (v) of this AD, provided that 
no MLG door actuator with a part number in figure 3 to paragraph (v) 
of this AD has been installed on that airplane since first flight, 
or since modification, as applicable.
    (2) An airplane in the configuration specified in paragraph 
(y)(1) of this AD, and with flight warning computers having P/N 
350E053021212 (H2F7) installed (Airbus Modification 153741 applied 
in production, or modified in service as specified in Airbus Service 
Bulletin A320-31-1414), is not affected by the requirement of 
paragraph (t) of this AD and, following modification, Airbus A318/
A319/A320/A321 TR TR437, L/G GEAR NOT DOWNLOCKED, Issue 1.0, dated 
May 23, 2014 (if inserted), may be removed from the AFM of that 
airplane.

(z) New Parts Installation Prohibitions

    (1) Except as specified in paragraph (z)(2) of this AD, as of 
the effective date of this AD, do not install on any airplane a MLG 
door actuator having a part number listed in figure 3 to paragraph 
(v) of this AD.
    (2) For an airplane subject to the requirements of paragraphs 
(u) and (v) of this AD, as applicable, do not install a MLG door 
actuator having a part number listed in figure 3 to paragraph (v) of 
this AD after modification of the airplane.
    (3) Except as specified in paragraph (z)(4) of this AD, as of 
the effective date of this AD, do not install on any airplane a 
flight warning computer (FWC) having a part number listed in figure 
4 to paragraph (z) of this AD.
    (4) For an airplane subject to the requirements of paragraphs 
(u) and (v) of this AD, as applicable, do not install a FWC having a 
part number listed in figure 4 to paragraph (z) of this AD after 
modification of the airplane.

       Figure 4 to Paragraph (z) of This AD--Affected Part Numbers
------------------------------------------------------------------------
               Component name                        Part number
------------------------------------------------------------------------
Flight warning computer....................           350E016187171 (C5)
                                                    350E017238484 (H1D1)
                                                    350E017248685 (H1D2)
                                                    350E017251414 (H1E1)
                                                    350E017271616 (H1E2)
                                                  350E018291818 (H1E3CJ)
                                                   350E018301919 (H1E3P)
                                                   350E018312020 (H1E3Q)
                                                    350E053020202 (H2E2)
                                                    350E053020303 (H2E3)
                                                    350E053020404 (H2E4)
                                                    350E053020606 (H2F2)
                                                    350E053020707 (H2F3)
                                                   350E053021010 (H2F3P)
                                                    350E053020808 (H2F4)
                                                    350E053020909 (H2F5)
                                                    350E053021111 (H2F6)
------------------------------------------------------------------------

(aa) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD, if those actions were performed before 
April 27, 2007 (the effective date of AD 2007-06-18), using Airbus 
Service Bulletin A320-32-1309, dated March 7, 2006. This service 
information is not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraphs (k), (l), and (m) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-32-1390, Revision 01, dated September 21, 2011; or 
Revision 02, dated October 23, 2013. Airbus Service Bulletin A320-
32-1390, Revision 01, dated September 21, 2011, was incorporated by 
reference in AD 2011-13-11. Airbus Service Bulletin A320-32-1390, 
Revision 02, dated October 23, 2013, is not incorporated by 
reference in this AD.
    (3) This paragraph provides credit for actions required by 
paragraphs (u) and (v) of this AD, if those actions were performed 
before the effective date of this AD using General Electric Service 
Bulletin 114122-32-105, dated January 17, 2013; or General Electric 
Service Bulletin 114122-32-105, Revision 1, dated March 26, 2013. 
This service information is not incorporated by reference in this 
AD.

(bb) 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 Airbus 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

[[Page 57129]]

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 require approval of 
an AMOC.
    (3) Contacting the Manufacturer: As of the effective date of 
this AD, except as specified in paragraph (j) of this AD for the use 
of an alternative method to check the PFR for CFDS messages, 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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (4) Previously Approved AMOCs: AMOCs approved previously for the 
AD 2011-13-11 and AD 2013-16-09 are approved as AMOCs for the 
corresponding provisions of this AD.

(cc) Special Flight Permits

    Special flight permits may be issued in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the airplane 
can be modified (if the operator elects to do so), provided the MLG 
remains extended and locked, and that no MLG recycle is done.

(dd) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0221, dated September 30, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0529-0003.
    (2) For Airbus 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.
    (3) For General Electric service information identified in this 
AD, contact GE Aviation, Customer Support Center, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
cs.techpubs@ge.com; Internet: http://www.geaviation.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.

    Issued in Renton, Washington, on August 21, 2015.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-21730 Filed 9-21-15; 8:45 am]
BILLING CODE 4910-13-P