Airworthiness Directives; Dassault Aviation Airplanes, 52545-52549 [2014-21037]

Download as PDF Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations conditions of this section have been met. (Approved by the Office of Management and Budget under control number 0579– 0387) Done in Washington, DC, this 28th day of August 2014. Kevin Shea, Administrator, Animal and Plant Health Inspection Service. [FR Doc. 2014–21113 Filed 9–3–14; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0464; Directorate Identifier 2012–NM–010–AD; Amendment 39–17947; AD 2014–16–23] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2011–16– 01 for all Dassault Aviation Model FALCON 7X airplanes. AD 2011–16–01 required adding an automatic reversion logic and a means for the pilot to override pitch trim control normal modes, and installing placards in the cockpit; replacing the frame of the emergency switch box; replacing certain horizontal stabilizer electronic control units (HSECU); revising the Limitations section of the airplane flight manual (AFM); and revising the maintenance program to incorporate a certain task. This new AD requires modifying the flyby-wire (FBW) standard; and operational testing of the electric motors reversion relays and trim emergency command of the horizontal stabilizer trim system (HSTS), and repairs if necessary. This AD was prompted by an uncontrolled pitch trim runaway during descent. We are issuing this AD to prevent an uncontrolled pitch trim runaway, which could result in loss of control of the airplane. DATES: This AD becomes effective October 9, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 9, 2014. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 16:31 Sep 03, 2014 Jkt 232001 this AD as of August 22, 2011 (76 FR 47424, August 5, 2011). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0464; or in person at the U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet http://www.dassaultfalcon.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. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). AD 2011–16–01 applied to all Dassault Aviation Model FALCON 7X airplanes. The NPRM published in the Federal Register on July 3, 2013 (78 FR 40065). The NPRM proposed to continue to require adding an automatic reversion logic and a means for the pilot to override pitch trim control normal modes, and installing placards in the cockpit; replacing the frame of the emergency switch box; replacing certain HSECU; revising the Limitations section of the AFM; and revising the maintenance program to incorporate a certain task. The NPRM also proposed to require modifying the FBW standard; operating the airplane according to the limitations and procedures in an approved AFM; and operational testing of the electric motors reversion relays and trim emergency command of the HSTS, and repairs if necessary. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2011–0241, dated December 19, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for all Dassault PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 52545 Aviation Model FALCON 7X airplanes. The MCAI states: In May 2011, a Dassault Aviation Falcon 7X aeroplane experienced an uncontrolled pitch trim runaway during descent. The crew succeeded in recovering a stable situation and performed an uneventful landing. The results of the investigations showed that there was a production defect in the Horizontal Stabilizer Electronic Control Unit (HSECU) which could have contributed to the cause of the event. This condition, if not corrected, could lead to a loss of control of the aeroplane. To address this unsafe condition, EASA issued emergency AD 2011–0102–E [http:// ad.easa.europa.eu/blob/easa_ad_2011_0102_ E_Superseded.pdf/EAD_2011-0102-E_1] which prohibited further flights. Following further technical investigations accomplished by Dassault Aviation, EASA issued AD 2011– 0114, currently at revision 2, [http:// ad.easa.europa.eu/blob/easa_ad_2011_ 0114R2.pdf/AD_2011-0114R2_1] which superseded EASA AD 2011–0102–E. Following accomplishment of all the actions as required by EASA AD 2011–0114R2, all aeroplanes could resume flying with operational limitations. Since EASA AD 2011–0114R2 was issued, Dassault Aviation have developed a modification (M1245 to be embodied through accomplishment of Dassault Aviation Service Bulletin F7X–214) of the Fly-By-Wire (FBW) current standard which improves the monitoring and reversion logic of the Horizontal Stabilizer Trim System (HSTS). This modification results in earlier failure detection and quicker reversion. Dassault Aviation have issued as well Revision 13 of the Aircraft Flight Manual (AFM) which incorporates the changes introduced in EASA AD 2011–0114R2 (CP55 and 56) as well as the new changes resulting from Dassault Aviation M1245 (CP58). Dassault Aviation have introduced as well operational tests of the HSTS electric motors reversion relays and of the HSTS trim emergency command into the Chapter 5.40 of F7X Aircraft Maintenance Manual (CP010). For the reasons described above, EASA issued [an AD] . . . to require: 1. Accomplishing Dassault Aviation modification M1245, 2. amending the AFM, and 3. implementing the operational tests of the HSTS electric motors reversion relays and of the HSTS trim emergency command. Accomplishment of all the above actions restored the full original certified flight envelope of the aeroplane. Since EASA AD 2011–0169 was issued, further analyses have demonstrated that, once Dassault Aviation modification M1245 is embodied, it is allowed to restore the originally certified Minimum Equipment List (MEL) items which were removed in accordance with the requirement of paragraph (4) of EASA AD 2011–0114R2. For the reasons described above, this [EASA] AD, which supersedes EASA AD 2011–0169, retaining its requirements, in addition, extends the applicability of the AD to all S/Ns and, for aeroplanes fitted with FBW standard 2.1.7.3, allows the MEL E:\FR\FM\04SER1.SGM 04SER1 52546 Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations limitations imposed by EASA AD 2011– 0114R2 to be removed. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-04640002. Comment We gave the public the opportunity to participate in developing this AD. We have considered the comment received. The following presents the comment received on the NPRM (78 FR 40065, July 3, 2013) and the FAA’s response to the comment. Request To Revise Unsafe Condition Determination Rockwell Collins requested that we remove the statement from the NPRM (78 FR 40065, July 3, 2013) that describes that the horizontal stabilizer electronic control unit could have contributed to the event which led to the determination of an unsafe condition. Rockwell Collins submitted a test report to substantiate its request. We disagree with the commenter’s request. As stated in the MCAI, the results of the investigations showed that there was a production defect in the HSECU, which could have contributed to the cause of the event. An airplane lost pitch control, which resulted in the unsafe condition determination that led to the issuance of the MCAI. We concur with the unsafe condition stated in the MCAI. We have not changed this final rule in this regard. mstockstill on DSK4VPTVN1PROD with RULES Revisions to Service Information Since we issued the NPRM (78 FR 40065, July 3, 2013), Dassault Aviation issued Chapter 5–40–00, Airworthiness Limitations, DGT 107838, Revision 3, dated July 16, 2012, of the Dassault Falcon 7X Maintenance Manual (MM); and Dassault Falcon 7X Airplane Flight Manual (AFM), DGT105608, Revision 18, dated November 15, 2013. These documents contain no substantive changes to the requirements of this final rule beyond the procedures specified in the revisions of the documents cited in the NPRM. We have determined that these new procedures will not impose an additional burden on any operator. This final rule has been changed to refer to this revised MM and AFM as the appropriate sources of information to address the identified unsafe condition. ‘‘Contacting the Manufacturer’’ Paragraph in This AD Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the VerDate Mar<15>2010 16:31 Sep 03, 2014 Jkt 232001 FAA develops an AD based on a foreign authority’s AD. We have become aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an ADmandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19. To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed the paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA, the European Aviation Safety Agency (EASA), or Dassault Aviation’s EASA Design Organization Approval (DOA). The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and information contained in the document are EASA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information. This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance. We also have decided not to include a generic reference to either the ‘‘delegated agent’’ or ‘‘design approval holder (DAH) with State of Design Authority design organization approval,’’ but instead we have provided the specific delegation approval granted by the State of Design Authority for the DAH throughout this AD. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 40065, July 3, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 40065, July 3, 2013). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 30 airplanes of U.S. registry. The actions that were required by AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011), that are retained in this AD take about 340 workhours per product, 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 2011– 16–01 is $28,900 per product. We also estimate that it will take about 11 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $28,050, or $935 per product. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue E:\FR\FM\04SER1.SGM 04SER1 Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. mstockstill on DSK4VPTVN1PROD with RULES Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0464; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Mar<15>2010 16:31 Sep 03, 2014 Jkt 232001 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011), and adding the following new AD: ■ 2014–16–23 Dassault Aviation: Amendment 39–17947. Docket No. FAA–2013–0464; Directorate Identifier 2012–NM–010–AD. (a) Effective Date This airworthiness directive (AD) becomes effective October 9, 2014. (b) Affected ADs This AD replaces AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). (c) Applicability This AD applies to all Dassault Aviation Model FALCON 7X airplanes, certificated in any category, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Reason This AD was prompted by an uncontrolled pitch trim runaway during descent. We are issuing this AD to prevent an uncontrolled pitch trim runaway, which could result in loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification This paragraph restates the requirements of paragraph (g) of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). Before further flight, do the applicable actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) For airplanes on which Dassault Mandatory Service Bulletin 7X–211, Revision 1, dated June 14, 2011, has not been done as of August 22, 2011 (the effective date of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011)): Modify the airplane by adding an automatic reversion logic and a means for the pilot to override pitch trim control normal modes, and install placards in the cockpit in full view of the pilots, in accordance with paragraph 2., ‘‘Accomplishment Instructions for Aircraft which have not Already Implemented the PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 52547 Revision 1 of the Service Bulletin,’’ of Dassault Mandatory Service Bulletin 7X–211, Revision 2, dated June 22, 2011, including New Standard Installation Checklist and Appendix A, and including FCS Data Loading Procedure, Issue D, dated May 28, 2010. (2) For airplanes on which Dassault Mandatory Service Bulletin 7X–211, Revision 1, dated June 14, 2011, has been done as of August 22, 2011 (the effective date of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011)): Replace the frame of the emergency switch box, in accordance with paragraph 3., ‘‘Accomplishment Instructions for Aircraft which have Already Implemented Revision 1 of this Service Bulletin,’’ of Dassault Mandatory Service Bulletin 7X–211, Revision 2, dated June 22, 2011, including New Standard Installation Checklist and Appendix A, and including FCS Data Loading Procedure, Issue D, dated May 28, 2010. (3) For airplanes equipped with any horizontal stabilizer electronic control unit (HSECU) part number (P/N) 051244–04, replace the HSECU with any HSECU identified in paragraph (g)(3)(i), (g)(3)(ii), or (g)(3)(iii) of this AD, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin 7X–212, Revision 2, dated July 7, 2011. (i) HSECU P/N 051244–02. (ii) Verified HSECU P/N 051244–04 having a stamped ‘‘V.’’ (iii) HSECU P/N 051244–05. (h) Retained Credit for Previous Actions This paragraph restates the provisions specified in paragraph (h) of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). This paragraph provides credit for the HSECU replacement required by paragraph (g)(3)(i) or (g)(3)(ii) of this AD, if those replacements were performed before August 22, 2011 (the effective date of AD 2011–16–01), using Dassault Mandatory Service Bulletin 7X–212, Revision 1, dated June 23, 2011, which is not incorporated by reference in this AD. (i) Retained Revision of Airplane Flight Manual (AFM) This paragraph restates the requirements of paragraph (i) of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). As of August 22, 2011 (the effective date AD 2011–16–01), operate the airplane according to the limitations and procedures in the Dassault Falcon 7X AFM, Revision 12, dated June 16, 2011, until the actions required by paragraph (p) of this AD are accomplished. Revision 12 introduces revised operational speed limitations and revised procedures accounting for the new TRIM EMERG button. (j) Retained Electronic Checklist Database Installation This paragraph restates the requirements of paragraph (j) of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). Before further flight, install the electronic checklist V0007 database, in accordance with the Accomplishment Instructions of Dassault Service Bulletin 7X–213, dated June 22, 2011. Accomplishing the actions required by E:\FR\FM\04SER1.SGM 04SER1 Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations paragraph (o) of this AD terminates the actions required by paragraph (j) of this AD. (k) Retained Operating Restrictions This paragraph restates the requirements of paragraph (k) of AD 2011–16–01, mstockstill on DSK4VPTVN1PROD with RULES (l) Retained Maintenance Program Revision This paragraph restates the requirements of paragraph (l) of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). (1) Within 30 days after August 22, 2011 (the effective date of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011)): Revise the maintenance program to incorporate Maintenance Planning Document (MPD) Task 27–40–00–710–801, as specified in Dassault Aviation, Falcon 7X Maintenance Manual (MM), Falcon 7X—Chapter 5–40–00 after Rev 01, dated June 10, 2011 (commonly referred to as Dassault Change Proposal (CP) CP009 to Chapter 5–40–00 of Dassault Falcon 7X MM). The initial compliance time for doing the operational test of the HSTS electric motors reversion relays is 1,850 flight hours after accomplishment of the applicable actions required by paragraph (g) of this AD. Accomplishment of the actions required in paragraph (q) of this AD terminates the actions required by paragraph (l) of this AD. (2) The MM revision required by paragraph (l) of this AD may be done by inserting a copy of Maintenance Planning Document (MPD) Task 27–40–00–710–801, as specified in Dassault Aviation, Falcon 7X Maintenance Manual (MM), Falcon 7X—Chapter 5–40–00 after Rev 01, dated June 10, 2011 (commonly referred to as Dassault Change Proposal (CP) CP009 to Chapter 5–40–00 of Dassault Falcon 7X MM), into the MM. When Dassault CP CP009 has been included in general revisions of the MM, the general revisions may be inserted into the MM, provided the relevant information in the general revision is identical to that in Dassault CP CP009, and Dassault CP CP009 may be removed. VerDate Mar<15>2010 16:31 Sep 03, 2014 Jkt 232001 Amendment 39–16759 (76 FR 47424, August 5, 2011). Before further flight, revise the Limitations section of the Dassault Falcon 7X AFM to include the information provided in figure 1 to paragraph (k) of this AD. This may be accomplished by inserting a copy of figure 1 to paragraph (k) of this AD into the AFM. Accomplishment of the actions required in paragraph (p) of this AD terminates the actions required by paragraph (k) of this AD. (m) Retained Limitations for Alternative Procedures or Intervals (o) New Fly-By-Wire System Modification This paragraph restates the requirements of paragraph (m) of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). After the maintenance program has been revised as required by paragraph (l) of this AD, no alternative procedure or interval for the operational test may be used unless the procedure and/or interval is approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (s) of this AD. (n) Retained FAA AD Differences This paragraph restates the AD differences identified in Note 3 of AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). This AD differs from the mandatory continuing airworthiness information (MCAI) and/or service information as follows: (1) European Aviation Safety Agency (EASA) AD 2011–0114R2, dated July 7, 2011, requires repetitive operational tests of the HSTS electric motors reversion relays, and specifies that the aircraft maintenance program may be revised in lieu of those repetitive tests. This FAA AD mandates revising the maintenance program. (2) EASA AD 2011–0114R2, dated July 7, 2011, does not include any requirement to revise the electronic checklist. Paragraph (j) of this FAA AD requires this action. (3) EASA AD 2011–0114R2, dated July 7, 2011, mandates amending the minimum equipment list (MEL) by removing certain items. This FAA AD instead requires revising the AFM to prohibit dispatch with those items inoperative. The operational effect, however, is the same. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Figure 1 to Paragraph (k) of this AD— Retained AFM Revision Within 12 months after accomplishing the actions required by paragraph (g) of this AD, or within 9 months after the effective date of this AD, whichever is later: Modify the flyby-wire system installed in the airplane to the 2.1.7.3 standard, in accordance with the Accomplishment Instructions of Dassault Service Bulletin 7X–214, dated August 30, 2011, as revised by Dassault Service Bulletin 7X–214, Erratum, dated January 26, 2012. Accomplishment of the actions required in paragraph (o) of this AD terminates the actions required by paragraph (j) of this AD. (p) New AFM Revision After accomplishing the actions required by paragraph (o) of this AD: Operate the airplane thereafter according to the limitations and procedures specified in Dassault Falcon 7X AFM, DGT105608, Revision 18, dated November 15, 2013. Accomplishment of the actions required by this paragraph terminates the requirements of paragraphs (i) and (k) of this AD; after those actions have been done, the AFM limitation required by paragraph (k) of this AD may be removed from the AFM. (q) New Maintenance Program Revision Within 30 days after the effective date of this AD: Revise the maintenance program to incorporate Chapter 5–40–00, Airworthiness Limitations, DGT 107838, Revision 3, dated July 16, 2012, of the Dassault Falcon 7X Maintenance Manual (MM), into the MM. (1) The initial compliance time for the operational test of the HSTS trim emergency command is within 650 flight hours after the modification required by paragraph (o) of this AD. E:\FR\FM\04SER1.SGM 04SER1 ER04SE14.017</GPH> 52548 Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations available at the addresses specified in paragraphs (u)(5) and (u)(6) of this AD. www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on August 7, 2014. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. (t) Related Information (1) Refer to MCAI EASA Airworthiness Directive 2011–0241, dated December 19, 2011. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2013-0464-0002. (2) Service information identified in this AD that is not incorporated by reference is (u) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on October 9, 2014. (i) Chapter 5–40–00, Airworthiness Limitations, DGT 107838, Revision 3, dated July 16, 2012, of the Dassault Falcon 7X Maintenance Manual (MM). (ii) Dassault Falcon 7X Airplane Flight Manual, DGT105608, Revision 18, dated November 15, 2013. The document revision level is identified only on the title page and page 1 of the List of Effective Sub-SubSections. The document date can only be found on the title page. (iii) Dassault Service Bulletin 7X–214, dated August 30, 2011. (iv) Dassault Service Bulletin 7X–214, Erratum, dated January 26, 2012. ‘‘Erratum’’ appears only in the list of effective/modified pages of this document. (4) The following service information was approved for IBR on August 22, 2011 (76 FR 47424, August 5, 2011). (i) Dassault Aviation, Falcon 7X Maintenance Manual, Falcon 7X—Chapter 5– 40–00 after Rev 01, dated June 10, 2011 (Commonly referred to as Dassault Change Proposal (CP) CP009 to Chapter 5–40–00 of Dassault Falcon 7X Maintenance Manual). (ii) Dassault Falcon 7X Airplane Flight Manual, Revision 12, dated June 16, 2011. The document date can only be found in the List of Revisions section of the Dassault Falcon 7X Airplane Flight Manual. (iii) Dassault Mandatory Service Bulletin 7X–211, Revision 2, dated June 22, 2011, including FCS Data Loading Procedure, Issue D, dated May 28, 2010, and including New Standard Installation Checklist and Appendix A,. New Standard Installation Checklist and Appendix A are not dated or identified with a document number. (iv) Dassault Mandatory Service Bulletin 7X–212, Revision 2, dated July 7, 2011. (v) Dassault Service Bulletin 7X–213, dated June 22, 2011. (5) For service information identified in this AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet http:// www.dassaultfalcon.com. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// 1 In a January 25, 2013 final rule document (78 FR 8362), the Commission announced that it would add ranges to the Rule for space-constrained products and small-duct, high-velocity systems. (2) The initial compliance time for the operational test of the HSTS electric motors reversion relays is within 5,050 flight hours after the modification required by paragraph (o) of this AD. (3) Accomplishment of the actions required in paragraph (q) of this AD terminates the actions required by paragraph (l) of this AD. (r) New Limitations for Alternative Actions or Intervals After accomplishing the revision required by paragraph (q) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (s) of this AD. (s) 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011), are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Dassault Aviation’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. mstockstill on DSK4VPTVN1PROD with RULES 52549 VerDate Mar<15>2010 16:31 Sep 03, 2014 Jkt 232001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 [FR Doc. 2014–21037 Filed 9–3–14; 8:45 am] BILLING CODE 4910–13–P FEDERAL TRADE COMMISSION 16 CFR Part 305 RIN 3084–AB03 Energy Labeling Rule Federal Trade Commission. Final rule; correction. AGENCY: ACTION: The Federal Trade Commission (‘‘Commission’’) is correcting a final rule published in the Federal Register of August 12, 2014, which amends the Energy Labeling Rule by updating comparability ranges for certain heating and cooling products and making conforming changes to the Rule’s sample labels. DATES: Effective Date: September 4, 2014. SUMMARY: FOR FURTHER INFORMATION CONTACT: Hampton Newsome, Attorney, Division of Enforcement, Bureau of Consumer Protection, Federal Trade Commission, Washington, DC 20580; (202) 326–2889. SUPPLEMENTARY INFORMATION: This document corrects tables and sample labels for central air conditioners in the August 12, 2014, final rule document (79 FR 46985) amending the Energy Labeling Rule (‘‘Rule’’), 16 CFR part 305. Specifically, this document corrects the lower range numbers for several central air conditioner categories to reflect new DOE minimum conservation standards scheduled for January 1, 2015, adds range numbers for space-constrained and small-duct, highvelocity product categories omitted from the tables in the final rule document,1 and makes conforming corrections to the range numbers on the sample labels. In FR Doc. 2014–18501, appearing in the Federal Register of Tuesday, August 12, 2014 (79 FR 46985), the following corrections are made: Appendix H to Part 305 [Corrected] 1. On page 46986, the table in Appendix H to Part 305 is corrected to read as follows: ■ E:\FR\FM\04SER1.SGM 04SER1

Agencies

[Federal Register Volume 79, Number 171 (Thursday, September 4, 2014)]
[Rules and Regulations]
[Pages 52545-52549]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-21037]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0464; Directorate Identifier 2012-NM-010-AD; 
Amendment 39-17947; AD 2014-16-23]
RIN 2120-AA64


Airworthiness Directives; Dassault Aviation Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2011-16-01 for 
all Dassault Aviation Model FALCON 7X airplanes. AD 2011-16-01 required 
adding an automatic reversion logic and a means for the pilot to 
override pitch trim control normal modes, and installing placards in 
the cockpit; replacing the frame of the emergency switch box; replacing 
certain horizontal stabilizer electronic control units (HSECU); 
revising the Limitations section of the airplane flight manual (AFM); 
and revising the maintenance program to incorporate a certain task. 
This new AD requires modifying the fly-by-wire (FBW) standard; and 
operational testing of the electric motors reversion relays and trim 
emergency command of the horizontal stabilizer trim system (HSTS), and 
repairs if necessary. This AD was prompted by an uncontrolled pitch 
trim runaway during descent. We are issuing this AD to prevent an 
uncontrolled pitch trim runaway, which could result in loss of control 
of the airplane.

DATES: This AD becomes effective October 9, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 9, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
22, 2011 (76 FR 47424, August 5, 2011).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0464; or in person at the 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC.
    For service information identified in this AD, contact Dassault 
Falcon Jet, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201-
440-6700; Internet http://www.dassaultfalcon.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.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1137; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-16-01, Amendment 39-16759 (76 FR 47424, 
August 5, 2011). AD 2011-16-01 applied to all Dassault Aviation Model 
FALCON 7X airplanes. The NPRM published in the Federal Register on July 
3, 2013 (78 FR 40065). The NPRM proposed to continue to require adding 
an automatic reversion logic and a means for the pilot to override 
pitch trim control normal modes, and installing placards in the 
cockpit; replacing the frame of the emergency switch box; replacing 
certain HSECU; revising the Limitations section of the AFM; and 
revising the maintenance program to incorporate a certain task. The 
NPRM also proposed to require modifying the FBW standard; operating the 
airplane according to the limitations and procedures in an approved 
AFM; and operational testing of the electric motors reversion relays 
and trim emergency command of the HSTS, and repairs if necessary.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2011-0241, dated December 19, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for all 
Dassault Aviation Model FALCON 7X airplanes. The MCAI states:

    In May 2011, a Dassault Aviation Falcon 7X aeroplane experienced 
an uncontrolled pitch trim runaway during descent. The crew 
succeeded in recovering a stable situation and performed an 
uneventful landing.
    The results of the investigations showed that there was a 
production defect in the Horizontal Stabilizer Electronic Control 
Unit (HSECU) which could have contributed to the cause of the event.
    This condition, if not corrected, could lead to a loss of 
control of the aeroplane.
    To address this unsafe condition, EASA issued emergency AD 2011-
0102-E [http://ad.easa.europa.eu/blob/
easaad20110102ESupersede
d.pdf/EAD2011-0102-E1] which prohibited further 
flights. Following further technical investigations accomplished by 
Dassault Aviation, EASA issued AD 2011-0114, currently at revision 
2, [http://ad.easa.europa.eu/blob/
easaad20110114R2.pdf/AD2011-
0114R21] which superseded EASA AD 2011-0102-E. Following 
accomplishment of all the actions as required by EASA AD 2011-
0114R2, all aeroplanes could resume flying with operational 
limitations.
    Since EASA AD 2011-0114R2 was issued, Dassault Aviation have 
developed a modification (M1245 to be embodied through 
accomplishment of Dassault Aviation Service Bulletin F7X-214) of the 
Fly-By-Wire (FBW) current standard which improves the monitoring and 
reversion logic of the Horizontal Stabilizer Trim System (HSTS). 
This modification results in earlier failure detection and quicker 
reversion.
    Dassault Aviation have issued as well Revision 13 of the 
Aircraft Flight Manual (AFM) which incorporates the changes 
introduced in EASA AD 2011-0114R2 (CP55 and 56) as well as the new 
changes resulting from Dassault Aviation M1245 (CP58).
    Dassault Aviation have introduced as well operational tests of 
the HSTS electric motors reversion relays and of the HSTS trim 
emergency command into the Chapter 5.40 of F7X Aircraft Maintenance 
Manual (CP010).
    For the reasons described above, EASA issued [an AD] . . . to 
require:
    1. Accomplishing Dassault Aviation modification M1245,
    2. amending the AFM, and
    3. implementing the operational tests of the HSTS electric 
motors reversion relays and of the HSTS trim emergency command.
    Accomplishment of all the above actions restored the full 
original certified flight envelope of the aeroplane.
    Since EASA AD 2011-0169 was issued, further analyses have 
demonstrated that, once Dassault Aviation modification M1245 is 
embodied, it is allowed to restore the originally certified Minimum 
Equipment List (MEL) items which were removed in accordance with the 
requirement of paragraph (4) of EASA AD 2011-0114R2.
    For the reasons described above, this [EASA] AD, which 
supersedes EASA AD 2011-0169, retaining its requirements, in 
addition, extends the applicability of the AD to all S/Ns and, for 
aeroplanes fitted with FBW standard 2.1.7.3, allows the MEL

[[Page 52546]]

limitations imposed by EASA AD 2011-0114R2 to be removed.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0464-0002.

Comment

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. The following 
presents the comment received on the NPRM (78 FR 40065, July 3, 2013) 
and the FAA's response to the comment.

Request To Revise Unsafe Condition Determination

    Rockwell Collins requested that we remove the statement from the 
NPRM (78 FR 40065, July 3, 2013) that describes that the horizontal 
stabilizer electronic control unit could have contributed to the event 
which led to the determination of an unsafe condition. Rockwell Collins 
submitted a test report to substantiate its request.
    We disagree with the commenter's request. As stated in the MCAI, 
the results of the investigations showed that there was a production 
defect in the HSECU, which could have contributed to the cause of the 
event. An airplane lost pitch control, which resulted in the unsafe 
condition determination that led to the issuance of the MCAI. We concur 
with the unsafe condition stated in the MCAI. We have not changed this 
final rule in this regard.

Revisions to Service Information

    Since we issued the NPRM (78 FR 40065, July 3, 2013), Dassault 
Aviation issued Chapter 5-40-00, Airworthiness Limitations, DGT 107838, 
Revision 3, dated July 16, 2012, of the Dassault Falcon 7X Maintenance 
Manual (MM); and Dassault Falcon 7X Airplane Flight Manual (AFM), 
DGT105608, Revision 18, dated November 15, 2013. These documents 
contain no substantive changes to the requirements of this final rule 
beyond the procedures specified in the revisions of the documents cited 
in the NPRM. We have determined that these new procedures will not 
impose an additional burden on any operator. This final rule has been 
changed to refer to this revised MM and AFM as the appropriate sources 
of information to address the identified unsafe condition.

``Contacting the Manufacturer'' Paragraph in This AD

    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD.
    We have become aware that some operators have misunderstood or 
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of 
deviations during the accomplishment of an AD-mandated action. The 
Airworthy Product paragraph does not approve messages or other 
information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed the paragraph and retitled 
it ``Contacting the Manufacturer.'' This paragraph now clarifies that 
for any requirement in this AD to obtain corrective actions from a 
manufacturer, the actions must be accomplished using a method approved 
by the FAA, the European Aviation Safety Agency (EASA), or Dassault 
Aviation's EASA Design Organization Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility previously afforded 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    We also have decided not to include a generic reference to either 
the ``delegated agent'' or ``design approval holder (DAH) with State of 
Design Authority design organization approval,'' but instead we have 
provided the specific delegation approval granted by the State of 
Design Authority for the DAH throughout this AD.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 40065, July 3, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 40065, July 3, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 30 airplanes of U.S. registry.
    The actions that were required by AD 2011-16-01, Amendment 39-16759 
(76 FR 47424, August 5, 2011), that are retained in this AD take about 
340 work-hours per product, at an average labor rate of $85 per work-
hour. Based on these figures, the estimated cost of the actions that 
were required by AD 2011-16-01 is $28,900 per product.
    We also estimate that it will take about 11 work-hours per product 
to comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $28,050, or $935 per product.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 52547]]

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

Regulatory Findings

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0464; or in person at the 
Docket Operations office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone (800) 
647-5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011), and 
adding the following new AD:

2014-16-23 Dassault Aviation: Amendment 39-17947. Docket No. FAA-
2013-0464; Directorate Identifier 2012-NM-010-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective October 9, 
2014.

(b) Affected ADs

    This AD replaces AD 2011-16-01, Amendment 39-16759 (76 FR 47424, 
August 5, 2011).

(c) Applicability

    This AD applies to all Dassault Aviation Model FALCON 7X 
airplanes, certificated in any category, all serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by an uncontrolled pitch trim runaway 
during descent. We are issuing this AD to prevent an uncontrolled 
pitch trim runaway, which could result in loss of control of the 
airplane.

(f) Compliance

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

(g) Retained Modification

    This paragraph restates the requirements of paragraph (g) of AD 
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). Before 
further flight, do the applicable actions specified in paragraphs 
(g)(1), (g)(2), and (g)(3) of this AD.
    (1) For airplanes on which Dassault Mandatory Service Bulletin 
7X-211, Revision 1, dated June 14, 2011, has not been done as of 
August 22, 2011 (the effective date of AD 2011-16-01, Amendment 39-
16759 (76 FR 47424, August 5, 2011)): Modify the airplane by adding 
an automatic reversion logic and a means for the pilot to override 
pitch trim control normal modes, and install placards in the cockpit 
in full view of the pilots, in accordance with paragraph 2., 
``Accomplishment Instructions for Aircraft which have not Already 
Implemented the Revision 1 of the Service Bulletin,'' of Dassault 
Mandatory Service Bulletin 7X-211, Revision 2, dated June 22, 2011, 
including New Standard Installation Checklist and Appendix A, and 
including FCS Data Loading Procedure, Issue D, dated May 28, 2010.
    (2) For airplanes on which Dassault Mandatory Service Bulletin 
7X-211, Revision 1, dated June 14, 2011, has been done as of August 
22, 2011 (the effective date of AD 2011-16-01, Amendment 39-16759 
(76 FR 47424, August 5, 2011)): Replace the frame of the emergency 
switch box, in accordance with paragraph 3., ``Accomplishment 
Instructions for Aircraft which have Already Implemented Revision 1 
of this Service Bulletin,'' of Dassault Mandatory Service Bulletin 
7X-211, Revision 2, dated June 22, 2011, including New Standard 
Installation Checklist and Appendix A, and including FCS Data 
Loading Procedure, Issue D, dated May 28, 2010.
    (3) For airplanes equipped with any horizontal stabilizer 
electronic control unit (HSECU) part number (P/N) 051244-04, replace 
the HSECU with any HSECU identified in paragraph (g)(3)(i), 
(g)(3)(ii), or (g)(3)(iii) of this AD, in accordance with the 
Accomplishment Instructions of Dassault Mandatory Service Bulletin 
7X-212, Revision 2, dated July 7, 2011.
    (i) HSECU P/N 051244-02.
    (ii) Verified HSECU P/N 051244-04 having a stamped ``V.''
    (iii) HSECU P/N 051244-05.

(h) Retained Credit for Previous Actions

    This paragraph restates the provisions specified in paragraph 
(h) of AD 2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 
2011). This paragraph provides credit for the HSECU replacement 
required by paragraph (g)(3)(i) or (g)(3)(ii) of this AD, if those 
replacements were performed before August 22, 2011 (the effective 
date of AD 2011-16-01), using Dassault Mandatory Service Bulletin 
7X-212, Revision 1, dated June 23, 2011, which is not incorporated 
by reference in this AD.

(i) Retained Revision of Airplane Flight Manual (AFM)

    This paragraph restates the requirements of paragraph (i) of AD 
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). As of 
August 22, 2011 (the effective date AD 2011-16-01), operate the 
airplane according to the limitations and procedures in the Dassault 
Falcon 7X AFM, Revision 12, dated June 16, 2011, until the actions 
required by paragraph (p) of this AD are accomplished. Revision 12 
introduces revised operational speed limitations and revised 
procedures accounting for the new TRIM EMERG button.

(j) Retained Electronic Checklist Database Installation

    This paragraph restates the requirements of paragraph (j) of AD 
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). Before 
further flight, install the electronic checklist V0007 database, in 
accordance with the Accomplishment Instructions of Dassault Service 
Bulletin 7X-213, dated June 22, 2011. Accomplishing the actions 
required by

[[Page 52548]]

paragraph (o) of this AD terminates the actions required by 
paragraph (j) of this AD.

(k) Retained Operating Restrictions

    This paragraph restates the requirements of paragraph (k) of AD 
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). Before 
further flight, revise the Limitations section of the Dassault 
Falcon 7X AFM to include the information provided in figure 1 to 
paragraph (k) of this AD. This may be accomplished by inserting a 
copy of figure 1 to paragraph (k) of this AD into the AFM. 
Accomplishment of the actions required in paragraph (p) of this AD 
terminates the actions required by paragraph (k) of this AD.

Figure 1 to Paragraph (k) of this AD--Retained AFM Revision
[GRAPHIC] [TIFF OMITTED] TR04SE14.017

(l) Retained Maintenance Program Revision

    This paragraph restates the requirements of paragraph (l) of AD 
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011).
    (1) Within 30 days after August 22, 2011 (the effective date of 
AD 2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011)): 
Revise the maintenance program to incorporate Maintenance Planning 
Document (MPD) Task 27-40-00-710-801, as specified in Dassault 
Aviation, Falcon 7X Maintenance Manual (MM), Falcon 7X--Chapter 5-
40-00 after Rev 01, dated June 10, 2011 (commonly referred to as 
Dassault Change Proposal (CP) CP009 to Chapter 5-40-00 of Dassault 
Falcon 7X MM). The initial compliance time for doing the operational 
test of the HSTS electric motors reversion relays is 1,850 flight 
hours after accomplishment of the applicable actions required by 
paragraph (g) of this AD. Accomplishment of the actions required in 
paragraph (q) of this AD terminates the actions required by 
paragraph (l) of this AD.
    (2) The MM revision required by paragraph (l) of this AD may be 
done by inserting a copy of Maintenance Planning Document (MPD) Task 
27-40-00-710-801, as specified in Dassault Aviation, Falcon 7X 
Maintenance Manual (MM), Falcon 7X--Chapter 5-40-00 after Rev 01, 
dated June 10, 2011 (commonly referred to as Dassault Change 
Proposal (CP) CP009 to Chapter 5-40-00 of Dassault Falcon 7X MM), 
into the MM. When Dassault CP CP009 has been included in general 
revisions of the MM, the general revisions may be inserted into the 
MM, provided the relevant information in the general revision is 
identical to that in Dassault CP CP009, and Dassault CP CP009 may be 
removed.

(m) Retained Limitations for Alternative Procedures or Intervals

    This paragraph restates the requirements of paragraph (m) of AD 
2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). After 
the maintenance program has been revised as required by paragraph 
(l) of this AD, no alternative procedure or interval for the 
operational test may be used unless the procedure and/or interval is 
approved as an alternative method of compliance (AMOC) in accordance 
with the procedures specified in paragraph (s) of this AD.

(n) Retained FAA AD Differences

    This paragraph restates the AD differences identified in Note 3 
of AD 2011-16-01, Amendment 39-16759 (76 FR 47424, August 5, 2011). 
This AD differs from the mandatory continuing airworthiness 
information (MCAI) and/or service information as follows:
    (1) European Aviation Safety Agency (EASA) AD 2011-0114R2, dated 
July 7, 2011, requires repetitive operational tests of the HSTS 
electric motors reversion relays, and specifies that the aircraft 
maintenance program may be revised in lieu of those repetitive 
tests. This FAA AD mandates revising the maintenance program.
    (2) EASA AD 2011-0114R2, dated July 7, 2011, does not include 
any requirement to revise the electronic checklist. Paragraph (j) of 
this FAA AD requires this action.
    (3) EASA AD 2011-0114R2, dated July 7, 2011, mandates amending 
the minimum equipment list (MEL) by removing certain items. This FAA 
AD instead requires revising the AFM to prohibit dispatch with those 
items inoperative. The operational effect, however, is the same.

(o) New Fly-By-Wire System Modification

    Within 12 months after accomplishing the actions required by 
paragraph (g) of this AD, or within 9 months after the effective 
date of this AD, whichever is later: Modify the fly-by-wire system 
installed in the airplane to the 2.1.7.3 standard, in accordance 
with the Accomplishment Instructions of Dassault Service Bulletin 
7X-214, dated August 30, 2011, as revised by Dassault Service 
Bulletin 7X-214, Erratum, dated January 26, 2012. Accomplishment of 
the actions required in paragraph (o) of this AD terminates the 
actions required by paragraph (j) of this AD.

(p) New AFM Revision

    After accomplishing the actions required by paragraph (o) of 
this AD: Operate the airplane thereafter according to the 
limitations and procedures specified in Dassault Falcon 7X AFM, 
DGT105608, Revision 18, dated November 15, 2013. Accomplishment of 
the actions required by this paragraph terminates the requirements 
of paragraphs (i) and (k) of this AD; after those actions have been 
done, the AFM limitation required by paragraph (k) of this AD may be 
removed from the AFM.

(q) New Maintenance Program Revision

    Within 30 days after the effective date of this AD: Revise the 
maintenance program to incorporate Chapter 5-40-00, Airworthiness 
Limitations, DGT 107838, Revision 3, dated July 16, 2012, of the 
Dassault Falcon 7X Maintenance Manual (MM), into the MM.
    (1) The initial compliance time for the operational test of the 
HSTS trim emergency command is within 650 flight hours after the 
modification required by paragraph (o) of this AD.

[[Page 52549]]

    (2) The initial compliance time for the operational test of the 
HSTS electric motors reversion relays is within 5,050 flight hours 
after the modification required by paragraph (o) of this AD.
    (3) Accomplishment of the actions required in paragraph (q) of 
this AD terminates the actions required by paragraph (l) of this AD.

(r) New Limitations for Alternative Actions or Intervals

    After accomplishing the revision required by paragraph (q) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used unless the actions or intervals are approved as an AMOC in 
accordance with the procedures specified in paragraph (s) of this 
AD.

(s) 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: Tom 
Rodriguez, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1137; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office. The AMOC approval letter must specifically 
reference this AD.
    (ii) AMOCs approved previously for AD 2011-16-01, Amendment 39-
16759 (76 FR 47424, August 5, 2011), are approved as AMOCs for the 
corresponding provisions of this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Dassault Aviation's EASA 
Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.

(t) Related Information

    (1) Refer to MCAI EASA Airworthiness Directive 2011-0241, dated 
December 19, 2011. You may examine the MCAI in the AD docket on the 
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-
0464-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (u)(5) and (u)(6) of this AD.

(u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
October 9, 2014.
    (i) Chapter 5-40-00, Airworthiness Limitations, DGT 107838, 
Revision 3, dated July 16, 2012, of the Dassault Falcon 7X 
Maintenance Manual (MM).
    (ii) Dassault Falcon 7X Airplane Flight Manual, DGT105608, 
Revision 18, dated November 15, 2013. The document revision level is 
identified only on the title page and page 1 of the List of 
Effective Sub-Sub-Sections. The document date can only be found on 
the title page.
    (iii) Dassault Service Bulletin 7X-214, dated August 30, 2011.
    (iv) Dassault Service Bulletin 7X-214, Erratum, dated January 
26, 2012. ``Erratum'' appears only in the list of effective/modified 
pages of this document.
    (4) The following service information was approved for IBR on 
August 22, 2011 (76 FR 47424, August 5, 2011).
    (i) Dassault Aviation, Falcon 7X Maintenance Manual, Falcon 7X--
Chapter 5-40-00 after Rev 01, dated June 10, 2011 (Commonly referred 
to as Dassault Change Proposal (CP) CP009 to Chapter 5-40-00 of 
Dassault Falcon 7X Maintenance Manual).
    (ii) Dassault Falcon 7X Airplane Flight Manual, Revision 12, 
dated June 16, 2011. The document date can only be found in the List 
of Revisions section of the Dassault Falcon 7X Airplane Flight 
Manual.
    (iii) Dassault Mandatory Service Bulletin 7X-211, Revision 2, 
dated June 22, 2011, including FCS Data Loading Procedure, Issue D, 
dated May 28, 2010, and including New Standard Installation 
Checklist and Appendix A,. New Standard Installation Checklist and 
Appendix A are not dated or identified with a document number.
    (iv) Dassault Mandatory Service Bulletin 7X-212, Revision 2, 
dated July 7, 2011.
    (v) Dassault Service Bulletin 7X-213, dated June 22, 2011.
    (5) For service information identified in this AD, contact 
Dassault Falcon Jet, P.O. Box 2000, South Hackensack, NJ 07606; 
telephone 201-440-6700; Internet http://www.dassaultfalcon.com.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 7, 2014.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-21037 Filed 9-3-14; 8:45 am]
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