47424 Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 

Issued in Burlington, Massachusetts on 

July 29, 2011. 

Colleen M. D’Alessandro, 

Acting Assistant Manager, Engine and 

Propeller Directorate Aircraft Certification 

Service. 

[FR Doc. 2011–19913 Filed 8–4–11; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0631; Directorate 

Identifier 2011–NM–134–AD; Amendment 

39–16759; AD 2011–16–01] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Model FALCON 7X Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Recently, 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. 

This condition, if occurring again, could 

lead to a loss of control of the aeroplane. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

August 22, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in the AD as 

of August 22, 2011. 

We must receive comments on this 

AD by September 19, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

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 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, 

Washington 98057–3356; phone: 425– 

227–1137; fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 16, 2011, we issued AD 

2011–12–51, Amendment 39–16735 (76 

FR 37251, June 27, 2011). To address an 

unsafe condition, that AD prohibited 

operation of the affected airplanes. That 

AD corresponds to Emergency 

Airworthiness Directive 2011–0102–E, 

dated May 26, 2011, issued by the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, to correct an unsafe 

condition for the specified products. 

Since we issued AD 2011–12–51, we 

have been advised of the development 

of new modifications that will address 

the unsafe condition. We have 

determined that these modifications are 

necessary to allow these airplanes to 

resume operation. The EASA issued 

Emergency AD 2011–0114–E, dated 

June 16, 2011, to supersede AD 2011– 

0102–E. The EASA subsequently 

revised that AD with EASA AD 2011– 

0114R1, dated June 23, 2011. The EASA 

subsequently revised that AD with 

EASA AD 2011–0114R2, dated July 7, 

2011 (referred to after this as ‘‘the 

MCAI’’), which states: 

Recently, 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. 

This condition, if occurring again, could 

lead to a loss of control of the aeroplane. 

To address this potential unsafe condition, 

pending investigations by the manufacturer, 

EASA issued emergency AD 2011–0102–E 

(which corresponds to FAA AD 2011–12–51) 

which prohibited further flights from its 

effective date. 

The initial results of the investigations 

show that there was a production defect in 

the Horizontal Stabilizer Electronic Control 

Unit (HSECU) which could have contributed 

to the cause of the event. There are two 

different HSECU part numbers (P/N) in use: 

P/N 051244–02 is not affected by this 

production defect and P/N 051244–04 is 

potentially affected by this production defect. 

The aeroplane that experienced the 

uncontrolled pitch trim runaway event was 

equipped with a HSECU P/N 051244–04. 

Investigations are continuing to confirm this 

cause. 

In the meantime, to allow re-starting flight 

operations and providing protection against 

further pitch trim runaway events, Dassault 

Aviation have developed two modifications 

(M1235 and M1236) which are implemented 

through accomplishment of Dassault 

Aviation Service Bulletin (SB) F7X–211. 

Furthermore, the flight envelope must be 

restricted, compared to the original certified 

flight envelope. Dassault Aviation have 

developed the corresponding Aircraft Flight 

Manual (AFM) limitations and a placard, to 

be installed in the cockpit (part of the 

instructions of SB F7X–211) to remind the 

flight crew of the limitations. In addition, 

modified operational procedures have been 

developed for in-flight activation of the new 

protection. 

A Certification Maintenance Requirement 

(CMR), to repetitively test the new Horizontal 

Stabilizer Trim Actuator (HSTA) electric 

motors reversion relays (installed with 

M1235 and M1236), has been developed and 

must be introduced into chapter 5.40 of the 

Aircraft Maintenance Manual (AMM). 

Additionally, the Master Minimum 

Equipment List (MMEL) is temporarily 

modified by this AD to prohibit dispatch of 

the aeroplane with some specific identified 

failures. 

To correct this unsafe condition and allow 

resumption of flights for aeroplanes equipped 

with HSECU P/N 051244–02, EASA issued 

AD 2011–0114–E, which superseded EASA 

AD 2011–0102–E, to require: 

1. Accomplishing two Dassault Aviation 

modifications, 

2. Amending the AFM and installing a 

placard in the cockpit, 

3. Amending the Minimum Equipment List 

(MEL), and 

4. Implementing an operational test of the 

HSTA electric motors reversion relays. 

For aeroplanes equipped with HSECU P/N 

051244–04, the prohibition of flights was 

maintained. 

Since EASA AD 2011–0114–E was issued, 

Dassault Aviation have issued SB F7X–212 

which gives instructions, for aeroplanes 

equipped with HSECU P/N 051244–04, to 

remove the HSECU for verification by 

Rockwell Collins and replace it with an 

HSECU that has passed the verification, 

having a name plate with a stamped V. After 


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Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 47425 

replacement of the HSECU P/N 051244–04 

with a verified HSECU P/N 051244–04 ‘‘V’’, 

the airplane can resume flights, provided the 

requirements of this AD are complied with. 

For the reasons described above, EASA AD 

2011–0114R1 was issued to allow aeroplanes 

equipped with HSECU P/N 051244–04 to 

resume flights under the same conditions as 

those previously established for aeroplanes 

equipped with HSECU P/N 051244–02, 

provided an HSECU P/N 051244–04 with 

stamped ‘‘V’’ is installed. 

Since EASA AD 2011–0114R1 was issued, 

Dassault Aviation have developed a 

modification of HSECU P/N 051244–04 

which corrects the production defect found 

on some of these units inspected during the 

initial investigation. This modified unit has 

a new P/N 051244–05 and it is eligible for 

installation on an aeroplane. 

For the reasons described above, this 

revised AD is issued to allow aeroplanes 

equipped with HSECU P/N 051244–05 to 

resume flights under the same conditions as 

those previously established for aeroplanes 

equipped with HSECU P/N 051244–02, or 

HSECU P/N 051244–04 with stamped ‘‘V.’’ 

This revised AD is still considered to be an 

interim measure. Pending results of the 

ongoing investigations, further AD action 

may follow to restore a fully certified flight 

envelope for aeroplanes of this type design. 

Required actions include revising the 

AFM to limit operation with certain 

inoperative MEL items, and revising the 

electronic checklist. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Dassault has issued 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; 

Mandatory Service Bulletin 7X–212, 

Revision 2, dated July 7, 2011; Service 

Bulletin 7X–213, dated June 22, 2011; 

Falcon 7X Airplane Flight Manual, 

Revision 12, dated June 16, 2011; and 

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). The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because of the possibility of an 

uncontrolled pitch trim runaway during 

descent, which could result in loss of 

control of the airplane. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2011–0631; 

Directorate Identifier 2011–NM–134– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 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 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); and 

3. 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 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. 

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. 


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47426 Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–16735 (76 FR 

37251, June 27, 2011) and adding the 

following new AD: 

2011–16–01 Dassault Aviation: 

Amendment 39–16759. Docket No. 

FAA–2011–0631; Directorate Identifier 

2011–NM–134–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 22, 2011. 

Affected ADs 

(b) This AD supersedes AD 2011–12–51, 

Amendment 39–16735. 

Applicability 

(c) This AD applies to all Dassault Aviation 

Model FALCON 7X airplanes, certificated in 

any category, all serial numbers. 

Note 1: 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 paragraph (n)(1) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

Recently, 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. 

This condition, if occurring again, could 

lead to a loss of control of the aeroplane. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Modification 

(g) 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 the effective date of this AD: 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 

the effective date of this AD: 

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 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) An HSECU replacement done before the 

effective date of this AD in accordance with 

Dassault Mandatory Service Bulletin 7X–212, 

Revision 1, dated June 23, 2011, is acceptable 

for compliance with the requirements of 

either paragraph (g)(3)(i) or (g)(3)(ii) of this 

AD. 

Revision of Airplane Flight Manual (AFM) 

(i) As of the effective date of this AD, 

operate the airplane according to the 

limitations and procedures in the Dassault 

Falcon 7X AFM, Revision 12, dated June 16, 

2011. Revision 12 introduces revised 

operational speed limitations and revised 

procedures accounting for the new TRIM 

EMERG button. 

Electronic Checklist Database Installation 

(j) 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. 

Operating Restrictions 

(k) Before further flight, revise the 

Limitations section of the Dassault Falcon 7X 

AFM to include the following information. 

This may be accomplished by inserting a 

copy of this AD into the AFM. 

‘‘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)’’ 

Maintenance Program Revision 

(l) Within 30 days after the effective date 

of this AD, revise the maintenance program 

to incorporate MPD task 27–40–00–710–801, 

as specified in 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). 

The initial compliance time for doing the 

operational test of the HSTA electric motors 

reversion relays is 1,850 flight hours after 

accomplishment of the applicable actions 

required by paragraph (g) of this AD. 

Note 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. 

No Alternative Procedures or Intervals 

(m) 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 AMOC in accordance with the procedures 

specified in paragraph (n) of this AD. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: 

(1) EASA AD 2011–0114R2 requires 

repetitive operational tests of the HSTA 

electric motors reversion relays, and specifies 

that the aircraft maintenance program may be 

revised in lieu of those repetitive tests. This 

FAA AD merely 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. 

Other FAA AD Provisions 

(n) 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 


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Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 47427 

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, Washington 98057– 

3356; phone: 425–227–1137; fax: 425–227– 

1149. 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 refer to 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 ensure the product is airworthy before it 

is returned to service. 

(3) Special Flight Permits: Special flight 

permits, as described in Section 21.197 and 

Section 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199), are 

allowed, if conducted in accordance with a 

method approved by the Manager, ANM–116, 

International Branch, Transport Airplane 

Directorate, FAA. 

Related Information 

(o) For related information, refer to MCAI 

EASA Airworthiness Directive 2011–0114R2, 

dated July 7, 2011, and the service 

information identified in table 1 of this AD. 

TABLE 1—RELATED INFORMATION

Document Revision Date 

Dassault Mandatory Service Bulletin 7X–211, including FCS Data Loading Procedure, Issue D, dated May 

28, 2010, New Standard Installation Checklist, and Appendix A.

2 June 22, 2011. 

Dassault Mandatory Service Bulletin 7X–212 ..................................................................................................... 2 July 7, 2011. 

Dassault Falcon 7X Airplane Flight Manual ........................................................................................................ 12 June 16, 2011. 

Dassault Service Bulletin 7X–213 ....................................................................................................................... .................... June 22, 2011. 

Dassault Aviation, Falcon 7x Maintenance Manual, Falcon 7X—Chapter 5–40–00 after Rev 01 (Commonly 

referred to as Dassault Change Proposal (CP) CP009 to Chapter 5–40–00 of Dassault Falcon 7X Maintenance Manual).

.................... June 10, 2011. 

Material Incorporated by Reference 

(p) You must use the service information 

contained in table 2 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. Appendix A and New 

Standard Installation Checklist of the 

Dassault Mandatory Service Bulletin 7X–211 

are not dated or identified with a document 

number. The document date can only be 

found in the List of Revisions section of the 

Dassault Falcon 7X Airplane Flight Manual. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(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 http:// 

www.dassaultfalcon.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Dassault Mandatory Service Bulletin 7X–211, including FCS Data Loading Procedure, Issue D, dated May 

28, 2010, New Standard Installation Checklist, and Appendix A.

2 June 22, 2011. 

Dassault Mandatory Service Bulletin 7X–212 ..................................................................................................... 2 July 7, 2011. 

Dassault Falcon 7X Airplane Flight Manual ........................................................................................................ 12 June 16, 2011. 

Dassault Service Bulletin 7X–213 ....................................................................................................................... .................... June 22, 2011. 

Dassault Aviation, Falcon 7x Maintenance Manual, Falcon 7X—Chapter 5–40–00 after Rev 01 (Commonly 

referred to as Dassault Change Proposal (CP) CP009 to Chapter 5–40–00 of Dassault Falcon 7X Maintenance Manual).

.................... June 10, 2011. 

Issued in Renton, Washington, on July 15, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–19866 Filed 8–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0041; Directorate 

Identifier 2010–NM–227–AD; Amendment 

39–16764; AD 2011–16–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–400 and –400F 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

a general visual inspection for cracks 

and holes of the main equipment center 

(MEC) drip shields, and repairs if 

necessary; installation of a fiberglass 

reinforcing overcoat; and, for certain 

airplanes, installation of stiffening 

panels to the MEC drip shields. This AD 

was prompted by a report of a loss of 

bus control unit number 1 and generator 

control units numbers 1 and 2 while the 

airplane was on the ground, and 

multiple operator reports of cracked 


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