Airworthiness Directive · Amendment 39-17947 · Flight controls
Dassault Aviation Airplanes
This AD applies to all Dassault Aviation Model FALCON 7X airplanes, certificated in any category, all serial numbers.
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.
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.
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.
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.
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 paragraph (o) of this AD terminates the actions required by paragraph (j) of this AD.
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.
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.
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.
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.
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.
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.
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.
(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.
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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
