Airworthiness Directives; Dassault Aviation Airplanes, 40065-40069 [2013-15949]

Download as PDF Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules (a) Applicability This AD applies to Erickson Air-Crane Incorporated (Erickson) Model S–64E and S– 64F helicopters, with rotary wing blade assembly (main rotor blade), part number (P/ N) 6415–20201–043, –045, –047, –048, –049, –050, or –051; or 6415–20601–041, –042, –043, –044, –045, –046, –047, –048, –049, –050, –051, or –052, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in the main rotor blade (blade), which could result in blade separation and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 90–26–12, Docket No. 90–ASW–27, Amendment 39–6841 (55 FR 51406, December 14, 1990). (d) Comments Due Date We must receive comments by September 3, 2013. tkelley on DSK3SPTVN1PROD with PROPOSALS (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) Before further flight, visually check the Blade Inspection Method (BIM) pressure indicators of the main rotor blades for a black or red color indication. (2) Before further flight, replace any blade with a black or red color indication in a BIM pressure indicator with an airworthy part of the same part number unless the black or red color indication is determined to be the result of BIM system malfunction. Note 1 to paragraph (f)(2) of this AD: Paragraphs (f)(4)(i–iv) of this AD specify how to determine if a BIM system is functioning correctly. (3) Repeat the visual BIM pressure indicator check required by paragraph (f)(1) of this AD prior to the first flight of each day and thereafter at intervals not to exceed: (i) Three hours time-in-service (TIS) from the last check for helicopters engaged in seven or more external lifts per hour; or (ii) Five hours TIS from the last check for helicopters engaged in either less than seven external lifts per hour or operation without external cargo. (4) Prior to the first flight of each day, check the BIM pressure indicator for proper function as follows: (i) Press in and hold the manual test lever (grenade-type handle) on the raised area of the handle over the pin-type actuation plunger. Do not handle the indicator glass bulb since the heat of the hand may change the internal reference pressure and result in an erroneous indicator reading. (ii) Depress the actuation plunger fully to shut off the pressure completely from the blade into the indicator. If necessary, press with the thumbs of both hands to overcome the plunger spring force. Note 2 to paragraph (f)(4)(ii) of this AD: If pressure is applied to the end of the lever on the flat area, the actuation plunger will not fully depress. VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 (iii) Verify proper operation of the indicator by observing that a full-black or full-red (unsafe) indication appears in not less than 10 or more than 30 seconds after depressing the plunger for a temperature of 20 degrees F (¥6.7 degrees C) or above. At lower temperatures, extend the upper limit to the corresponding time as follows: (A) 19 to 0 degrees F (¥7.2 to ¥17.8 degrees C); upper limit of 35 seconds. (B) ¥1 to ¥20 degrees F (¥18.3 to ¥28.9 degrees C); upper limit of 40 seconds. (C) ¥21 to ¥40 degrees F (¥29.4 to ¥40.0 degrees C); upper limit of 50 seconds. (D) ¥41 to ¥60 degrees F (¥40.5 to ¥51.1 degrees C); upper limit of 60 seconds. (iv) Release the lever and observe that the black or red indication snaps back immediately, leaving an all-white or allyellow (safe) indication. (v) If the indicator does not meet the specified requirements, then either identify and correct the BIM indicator malfunction or replace the suspect main rotor blade with an airworthy blade of the same part number prior to further flight. (5) The checks required by paragraphs (f)(1) and (f)(4)(i–iv) of this AD may be performed by the owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1)–(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (g) Special Flight Permit Special flight permits will not be issued. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: JC Lin, Aviation Safety Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5170; email 7-AVSASW-170@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (i) Additional Information Erickson Air-Crane Incorporated Service Bulletins No. 64B15–4D, Revision D, dated January 26, 2001 for the Model S–64E and No. 64F15–2, Revision A, dated July 14, 1999 for the Model S–64F, which are not incorporated by reference, contain additional information about the subject of this AD. For service information, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson/ Compliance Officer, 3100 Willow Springs Rd, PO Box 3247, Central Point, OR 97502; telephone (541) 664–5544; fax (541) 664– 2312; email cerickson@ericksonaircrane.com. You may review a copy of this information at the FAA, Office of the Regional Counsel, PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 40065 Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (j) Subject Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blades. Issued in Fort Worth, Texas, on June 18, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–15954 Filed 7–2–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0464; Directorate Identifier 2012–NM–010–AD] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to all Dassault Aviation Model FALCON 7X airplanes. The existing AD currently requires 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); operating the airplane according to the limitations and procedures in the airplane flight manual (AFM); revising the Limitations section of the AFM; and revising the maintenance program to incorporate a certain maintenance planning document (MPD) task. Since we issued that AD, Dassault Aviation has developed a modification of the fly-by-wire (FBW) standard; changed the AFM to incorporate changes resulting from the FBW modification; and revised the airplane maintenance manual (AMM) to incorporate repetitive operational tests of the electric motors reversion relays and trim emergency command of the horizontal stabilizer trim system (HSTS). Once incorporated, these actions allow restoration of the originally certified minimum equipment list items. This proposed AD would retain certain requirements of the previous AD; would require modifying the FBW standard; operating the SUMMARY: E:\FR\FM\03JYP1.SGM 03JYP1 40066 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 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. We are proposing this AD to prevent an uncontrolled pitch trim runaway, which could result in loss of control of the airplane. DATES: We must receive comments on this proposed AD by August 19, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606; telephone 201–440–6700; Internet https://www.dassaultfalcon.com. You may review copies of the 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. tkelley on DSK3SPTVN1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: 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: VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 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–2013–0464; Directorate Identifier 2012–NM–010–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 https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On July 15, 2011, we issued AD 2011– 16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). That AD requires actions intended to address an unsafe condition on all Dassault Aviation Model FALCON 7X airplanes. Since we issued AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011), 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 the specified products. 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 which prohibited further flights. Following further technical investigations accomplished by Dassault Aviation, EASA issued AD 2011– 0114, currently at revision 2, 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 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 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 AD 2011–0169 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 limitations imposed by EASA AD 2011– 0114R2 to be removed. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Dassault has issued the following service information. • Dassault Mandatory Service Bulletin 7X–214, including New Standard Installation Checklist, dated August 30, 2011. • Dassault Mandatory Service Bulletin 7X–214, Revision Erratum, dated January 26, 2012. • Dassault Falcon 7X AFM, Revision 13, dated August 29, 2011. • FCS Data Loading Procedure, Reference DT EQUIP 43913, Issue D, dated May 28, 2010. • Chapter 5–40–00, Airworthiness Limitations, of the Falcon 7X Maintenance Manual DGT 107838, Revision 2, dated August 25, 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. Explanation of Changes Made to This NPRM We have revised the heading and wording for paragraph (h) of this E:\FR\FM\03JYP1.SGM 03JYP1 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules proposed AD; this change does not affect the intent of that paragraph. We have deleted note 2 to paragraph (l) of AD 2011–16–01, Amendment 39– 16759 (76 FR 47424, August 5, 2011). Instead, we have included that information in paragraph (l)(2) of this proposed AD. We have deleted note 3 of AD 2011– 16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011). Instead, we have included that information in paragraph (n) of this proposed AD. tkelley on DSK3SPTVN1PROD with PROPOSALS FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to the procedures specified in paragraph (s) of this proposed AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 30 products of U.S. registry. The actions that are required by AD 2011–16–01, Amendment 39–16759 (76 FR 47424, August 5, 2011), and retained in this proposed AD take about 340 work-hours per product, at an average labor rate of $85 per work hour. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, the estimated cost of VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 the currently required actions is $28,900 product. We estimate that it would take about 11 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $28,050, or $935 per product. 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. PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 40067 We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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. § 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: ■ Dassault Aviation: Docket No. FAA–2013– 0464; Directorate Identifier 2012–NM– 010–AD. (a) Comments Due Date We must receive comments by August 19, 2013. (b) Affected ADs This AD supersedes 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 You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Retained Modification This paragraph restates the requirements of paragraph (g) of AD 2011–16–01, Amendment 39–16759 (76 FR47424, 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 E:\FR\FM\03JYP1.SGM 03JYP1 40068 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 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, including New Standard Installation Checklist and Appendix A, dated June 22, 2011, 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, including New Standard Installation Checklist and Appendix A, dated June 22, 2011, including FCS Data Loading Procedure, Issue D, dated May 28, 2010. (3) For airplanes equipped with any horizontal stabilizer electronic control unit (HSECU) 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. tkelley on DSK3SPTVN1PROD with PROPOSALS (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. VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 (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. Accomplishment of the actions required in 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 Dispatch with any inoperative equipment identified below is prohibited. This prohibition takes precedence over the FAA master minimum equipment list (MMEL) or any operator’s MEL. Air data systems (identified as MEL item 34– 9) Multi functional probe (MFP) heating system (identified as MMEL item 30–1) ACMU3 and ACMU4 (identified as MMEL item 27–3) LH REAR POWER #3 (identified as MMEL item 27–5–(–6) Back-up mode (identified as MMEL item 27– 8) (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 Dassault CP CP009, dated June 10, 2011, 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 PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 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 FR47424, 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 by 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 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 does not include any requirement to revise the electronic checklist. Paragraph (j) of this FAA AD requires this action. (3) EASA AD 2011–0114R2 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 flyby-wire system installed in the airplane to the 2.1.7.3 standard, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin 7X–214, dated August 30, 2011, as revised by Dassault Mandatory Service Bulletin 7X–214, Revision 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, Revision 13, dated August 29, 2011. Accomplishment of the actions required by this paragraph terminates the requirements of paragraphs (i) and (k) of this AD; thereafter, 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 E:\FR\FM\03JYP1.SGM 03JYP1 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules incorporate Chapter 5–40–00, Airworthiness Limitations, of the Dassault Falcon 7X MM DGT 107838, Revision 2, dated August 25, 2011, 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. (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. tkelley on DSK3SPTVN1PROD with PROPOSALS (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, Transport Airplane Directorate, ANM–116, 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: 9ANM-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. AMOCs approved previously in accordance with 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (t) Related Information (1) Refer to MCAI EASA Airworthiness Directive 2011–0241, dated December 19, 2011, and the service information specified in paragraphs (t)(1)(i) though (t)(1)(ix) of this AD. VerDate Mar<15>2010 16:18 Jul 02, 2013 Jkt 229001 (i) Chapter 5–40–00, Airworthiness Limitations, of the Dassault Falcon 7X MM DGT 107838, Revision 2, dated August 25, 2011. (ii) Dassault Change Proposal CP009 to Chapter 5–40- 00 of Dassault Falcon 7X Maintenance Manual), dated June 10, 2011. (iii) Dassault Falcon 7X Airplane Flight Manual, Revision 12, dated June 16, 2011. (iv) Dassault Falcon 7X Airplane Flight Manual, Revision 13, dated August 29, 2011. (v) Dassault Mandatory Service Bulletin 7X–211, Revision 2, including New Standard Installation Checklist and Appendix A, dated June 22, 2011, including FCS Data Loading Procedure, Issue D, dated May 28, 2010. (vi) Dassault Mandatory Service Bulletin 7X–212, Revision 2, dated July 7, 2011. (vii) Dassault Mandatory Service Bulletin 7X–214, dated August 30, 2011. (viii) Dassault Mandatory Service Bulletin 7X–214, Revision Erratum, dated January 26, 2012. (ix) Dassault Service Bulletin 7X–213, dated June 22, 2011. (2) For service information identified in this AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606; telephone 201–440–6700; Internet https:// www.dassaultfalcon.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on June 14, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–15949 Filed 7–2–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0539; Directorate Identifier 2012–NM–145–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of Proposed Rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2000–12– 11, that applies to certain Model A300 B4–600 and Model A300 B4–600R series airplanes. That AD currently requires repetitive inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair if necessary. Since we issued that AD, we have determined through a fleet survey SUMMARY: PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 40069 and an updated fatigue and damage tolerance analysis that the risk for fatigue cracking on the front and rear spar bottom booms is higher than was initially determined. This proposed AD would reduce the initial inspection compliance time and repetitive inspection interval. We are proposing this AD to detect and correct fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar. DATES: We must receive comments on this proposed AD by August 19, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS— EAW (Airworthiness Office), 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 https://www.airbus.com. You may review copies of the 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 https:// www.regulations.gov; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 227–2125; fax: (425) 227–1149. E:\FR\FM\03JYP1.SGM 03JYP1

Agencies

[Federal Register Volume 78, Number 128 (Wednesday, July 3, 2013)]
[Proposed Rules]
[Pages 40065-40069]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-15949]


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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]
RIN 2120-AA64


Airworthiness Directives; Dassault Aviation Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to all Dassault Aviation Model FALCON 7X airplanes. 
The existing AD currently requires 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); operating the airplane according to 
the limitations and procedures in the airplane flight manual (AFM); 
revising the Limitations section of the AFM; and revising the 
maintenance program to incorporate a certain maintenance planning 
document (MPD) task. Since we issued that AD, Dassault Aviation has 
developed a modification of the fly-by-wire (FBW) standard; changed the 
AFM to incorporate changes resulting from the FBW modification; and 
revised the airplane maintenance manual (AMM) to incorporate repetitive 
operational tests of the electric motors reversion relays and trim 
emergency command of the horizontal stabilizer trim system (HSTS). Once 
incorporated, these actions allow restoration of the originally 
certified minimum equipment list items. This proposed AD would retain 
certain requirements of the previous AD; would require modifying the 
FBW standard; operating the

[[Page 40066]]

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. We 
are proposing this AD to prevent an uncontrolled pitch trim runaway, 
which could result in loss of control of the airplane.

DATES: We must receive comments on this proposed AD by August 19, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606; 
telephone 201-440-6700; Internet https://www.dassaultfalcon.com.
    You may review copies of the 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 https://www.regulations.gov; 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: 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:

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-2013-0464; 
Directorate Identifier 2012-NM-010-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 https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On July 15, 2011, we issued AD 2011-16-01, Amendment 39-16759 (76 
FR 47424, August 5, 2011). That AD requires actions intended to address 
an unsafe condition on all Dassault Aviation Model FALCON 7X airplanes.
    Since we issued AD 2011-16-01, Amendment 39-16759 (76 FR 47424, 
August 5, 2011), 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 the specified products. 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 which prohibited further flights. Following further technical 
investigations accomplished by Dassault Aviation, EASA issued AD 
2011-0114, currently at revision 2, 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 AD 2011-0169 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 
limitations imposed by EASA AD 2011-0114R2 to be removed.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Dassault has issued the following service information.
     Dassault Mandatory Service Bulletin 7X-214, including New 
Standard Installation Checklist, dated August 30, 2011.
     Dassault Mandatory Service Bulletin 7X-214, Revision 
Erratum, dated January 26, 2012.
     Dassault Falcon 7X AFM, Revision 13, dated August 29, 
2011.
     FCS Data Loading Procedure, Reference DT EQUIP 43913, 
Issue D, dated May 28, 2010.
     Chapter 5-40-00, Airworthiness Limitations, of the Falcon 
7X Maintenance Manual DGT 107838, Revision 2, dated August 25, 2011. 
The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

Explanation of Changes Made to This NPRM

    We have revised the heading and wording for paragraph (h) of this

[[Page 40067]]

proposed AD; this change does not affect the intent of that paragraph.
    We have deleted note 2 to paragraph (l) of AD 2011-16-01, Amendment 
39-16759 (76 FR 47424, August 5, 2011). Instead, we have included that 
information in paragraph (l)(2) of this proposed AD.
    We have deleted note 3 of AD 2011-16-01, Amendment 39-16759 (76 FR 
47424, August 5, 2011). Instead, we have included that information in 
paragraph (n) of this proposed AD.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    This AD requires revisions to certain operator maintenance 
documents to include new inspections. Compliance with these inspections 
is required by 14 CFR 91.403(c). For airplanes that have been 
previously modified, altered, or repaired in the areas addressed by 
these inspections, the operator may not be able to accomplish the 
inspections described in the revisions. In this situation, to comply 
with 14 CFR 91.403(c), the operator must request approval for an 
alternative method of compliance according to the procedures specified 
in paragraph (s) of this proposed AD. The request should include a 
description of changes to the required inspections that will ensure the 
continued operational safety of the airplane.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 30 products of U.S. registry.
    The actions that are required by AD 2011-16-01, Amendment 39-16759 
(76 FR 47424, August 5, 2011), and retained in this proposed AD take 
about 340 work-hours per product, at an average labor rate of $85 per 
work hour. Where the service information lists required parts costs 
that are covered under warranty, we have assumed that there will be no 
charge for these parts. As we do not control warranty coverage for 
affected parties, some parties may incur costs higher than estimated 
here. Based on these figures, the estimated cost of the currently 
required actions is $28,900 product.
    We estimate that it would take about 11 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Where the service information lists 
required parts costs that are covered under warranty, we have assumed 
that there will be no charge for these parts. As we do not control 
warranty coverage for affected parties, some parties may incur costs 
higher than estimated here. Based on these figures, we estimate the 
cost of the proposed AD on U.S. operators to be $28,050, or $935 per 
product.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Dassault Aviation: Docket No. FAA-2013-0464; Directorate Identifier 
2012-NM-010-AD.

(a) Comments Due Date

    We must receive comments by August 19, 2013.

(b) Affected ADs

    This AD supersedes 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

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Modification

    This paragraph restates the requirements of paragraph (g) of AD 
2011-16-01, Amendment 39-16759 (76 FR47424, 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

[[Page 40068]]

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, including 
New Standard Installation Checklist and Appendix A, dated June 22, 
2011, 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, including New Standard Installation Checklist 
and Appendix A, dated June 22, 2011, including FCS Data Loading 
Procedure, Issue D, dated May 28, 2010.
    (3) For airplanes equipped with any horizontal stabilizer 
electronic control unit (HSECU) 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. Accomplishment of the actions 
required in 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

    Dispatch with any inoperative equipment identified below is 
prohibited. This prohibition takes precedence over the FAA master 
minimum equipment list (MMEL) or any operator's MEL.

Air data systems (identified as MEL item 34-9)
Multi functional probe (MFP) heating system (identified as MMEL item 
30-1)
ACMU3 and ACMU4 (identified as MMEL item 27-3)
LH REAR POWER 3 (identified as MMEL item 27-5-(-6)
Back-up mode (identified as MMEL item 27-8)

(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 Dassault CP CP009, dated June 10, 2011, 
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 FR47424, 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 by 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 
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 does not include any requirement to 
revise the electronic checklist. Paragraph (j) of this FAA AD 
requires this action.
    (3) EASA AD 2011-0114R2 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 Mandatory Service 
Bulletin 7X-214, dated August 30, 2011, as revised by Dassault 
Mandatory Service Bulletin 7X-214, Revision 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, 
Revision 13, dated August 29, 2011. Accomplishment of the actions 
required by this paragraph terminates the requirements of paragraphs 
(i) and (k) of this AD; thereafter, 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

[[Page 40069]]

incorporate Chapter 5-40-00, Airworthiness Limitations, of the 
Dassault Falcon 7X MM DGT 107838, Revision 2, dated August 25, 2011, 
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.
    (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, Transport Airplane Directorate, ANM-116, 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. 
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. AMOCs approved previously in accordance with 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(t) Related Information

    (1) Refer to MCAI EASA Airworthiness Directive 2011-0241, dated 
December 19, 2011, and the service information specified in 
paragraphs (t)(1)(i) though (t)(1)(ix) of this AD.
    (i) Chapter 5-40-00, Airworthiness Limitations, of the Dassault 
Falcon 7X MM DGT 107838, Revision 2, dated August 25, 2011.
    (ii) Dassault Change Proposal CP009 to Chapter 5-40- 00 of 
Dassault Falcon 7X Maintenance Manual), dated June 10, 2011.
    (iii) Dassault Falcon 7X Airplane Flight Manual, Revision 12, 
dated June 16, 2011.
    (iv) Dassault Falcon 7X Airplane Flight Manual, Revision 13, 
dated August 29, 2011.
    (v) Dassault Mandatory Service Bulletin 7X-211, Revision 2, 
including New Standard Installation Checklist and Appendix A, dated 
June 22, 2011, including FCS Data Loading Procedure, Issue D, dated 
May 28, 2010.
    (vi) Dassault Mandatory Service Bulletin 7X-212, Revision 2, 
dated July 7, 2011.
    (vii) Dassault Mandatory Service Bulletin 7X-214, dated August 
30, 2011.
    (viii) Dassault Mandatory Service Bulletin 7X-214, Revision 
Erratum, dated January 26, 2012.
    (ix) Dassault Service Bulletin 7X-213, dated June 22, 2011.
    (2) For service information identified in this AD, contact 
Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 
07606; telephone 201-440-6700; Internet https://www.dassaultfalcon.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, WA. For information on the availability of 
this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on June 14, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-15949 Filed 7-2-13; 8:45 am]
BILLING CODE 4910-13-P