Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations 52545 

conditions of this section have been 

met. 

(Approved by the Office of Management 

and Budget under control number 0579– 

0387) 

Done in Washington, DC, this 28th day of 

August 2014. 

Kevin Shea, 

Administrator, Animal and Plant Health 

Inspection Service. 

[FR Doc. 2014–21113 Filed 9–3–14; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0464; Directorate 

Identifier 2012–NM–010–AD; Amendment 

39–17947; AD 2014–16–23] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–16– 

01 for all Dassault Aviation Model 

FALCON 7X airplanes. AD 2011–16–01 

required adding an automatic reversion 

logic and a means for the pilot to 

override pitch trim control normal 

modes, and installing placards in the 

cockpit; replacing the frame of the 

emergency switch box; replacing certain 

horizontal stabilizer electronic control 

units (HSECU); revising the Limitations 

section of the airplane flight manual 

(AFM); and revising the maintenance 

program to incorporate a certain task. 

This new AD requires modifying the flyby-wire (FBW) standard; and 

operational testing of the electric motors 

reversion relays and trim emergency 

command of the horizontal stabilizer 

trim system (HSTS), and repairs if 

necessary. This AD was prompted by an 

uncontrolled pitch trim runaway during 

descent. We are issuing this AD to 

prevent an uncontrolled pitch trim 

runaway, which could result in loss of 

control of the airplane. 

DATES: This AD becomes effective 

October 9, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 9, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 22, 2011 (76 FR 

47424, August 5, 2011). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0464; or in 

person at the U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Dassault Falcon Jet, 

P.O. Box 2000, South Hackensack, NJ 

07606; telephone 201–440–6700; 

Internet http://www.dassaultfalcon.com. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, 

August 5, 2011). AD 2011–16–01 

applied to all Dassault Aviation Model 

FALCON 7X airplanes. The NPRM 

published in the Federal Register on 

July 3, 2013 (78 FR 40065). The NPRM 

proposed to continue to require adding 

an automatic reversion logic and a 

means for the pilot to override pitch 

trim control normal modes, and 

installing placards in the cockpit; 

replacing the frame of the emergency 

switch box; replacing certain HSECU; 

revising the Limitations section of the 

AFM; and revising the maintenance 

program to incorporate a certain task. 

The NPRM also proposed to require 

modifying the FBW standard; operating 

the airplane according to the limitations 

and procedures in an approved AFM; 

and operational testing of the electric 

motors reversion relays and trim 

emergency command of the HSTS, and 

repairs if necessary. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0241, 

dated December 19, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for all Dassault 

Aviation Model FALCON 7X airplanes. 

The MCAI states: 

In May 2011, a Dassault Aviation Falcon 

7X aeroplane experienced an uncontrolled 

pitch trim runaway during descent. The crew 

succeeded in recovering a stable situation 

and performed an uneventful landing. 

The results of the investigations showed 

that there was a production defect in the 

Horizontal Stabilizer Electronic Control Unit 

(HSECU) which could have contributed to 

the cause of the event. 

This condition, if not corrected, could lead 

to a loss of control of the aeroplane. 

To address this unsafe condition, EASA 

issued emergency AD 2011–0102–E [http://

ad.easa.europa.eu/blob/easa_ad_2011_0102_

E_Superseded.pdf/EAD_2011-0102-E_1] 

which prohibited further flights. Following 

further technical investigations accomplished 

by Dassault Aviation, EASA issued AD 2011– 

0114, currently at revision 2, [http://

ad.easa.europa.eu/blob/easa_ad_2011_

0114R2.pdf/AD_2011-0114R2_1] which 

superseded EASA AD 2011–0102–E. 

Following accomplishment of all the actions 

as required by EASA AD 2011–0114R2, all 

aeroplanes could resume flying with 

operational limitations. 

Since EASA AD 2011–0114R2 was issued, 

Dassault Aviation have developed a 

modification (M1245 to be embodied through 

accomplishment of Dassault Aviation Service 

Bulletin F7X–214) of the Fly-By-Wire (FBW) 

current standard which improves the 

monitoring and reversion logic of the 

Horizontal Stabilizer Trim System (HSTS). 

This modification results in earlier failure 

detection and quicker reversion. 

Dassault Aviation have issued as well 

Revision 13 of the Aircraft Flight Manual 

(AFM) which incorporates the changes 

introduced in EASA AD 2011–0114R2 (CP55 

and 56) as well as the new changes resulting 

from Dassault Aviation M1245 (CP58). 

Dassault Aviation have introduced as well 

operational tests of the HSTS electric motors 

reversion relays and of the HSTS trim 

emergency command into the Chapter 5.40 of 

F7X Aircraft Maintenance Manual (CP010). 

For the reasons described above, EASA 

issued [an AD] . . . to require: 

1. Accomplishing Dassault Aviation 

modification M1245, 

2. amending the AFM, and 

3. implementing the operational tests of the 

HSTS electric motors reversion relays and of 

the HSTS trim emergency command. 

Accomplishment of all the above actions 

restored the full original certified flight 

envelope of the aeroplane. 

Since EASA AD 2011–0169 was issued, 

further analyses have demonstrated that, 

once Dassault Aviation modification M1245 

is embodied, it is allowed to restore the 

originally certified Minimum Equipment List 

(MEL) items which were removed in 

accordance with the requirement of 

paragraph (4) of EASA AD 2011–0114R2. 

For the reasons described above, this 

[EASA] AD, which supersedes EASA AD 

2011–0169, retaining its requirements, in 

addition, extends the applicability of the AD 

to all S/Ns and, for aeroplanes fitted with 

FBW standard 2.1.7.3, allows the MEL 

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52546 Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations 

limitations imposed by EASA AD 2011– 

0114R2 to be removed. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0464- 

0002. 

Comment 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The following presents the comment 

received on the NPRM (78 FR 40065, 

July 3, 2013) and the FAA’s response to 

the comment. 

Request To Revise Unsafe Condition 

Determination 

Rockwell Collins requested that we 

remove the statement from the NPRM 

(78 FR 40065, July 3, 2013) that 

describes that the horizontal stabilizer 

electronic control unit could have 

contributed to the event which led to 

the determination of an unsafe 

condition. Rockwell Collins submitted a 

test report to substantiate its request. 

We disagree with the commenter’s 

request. As stated in the MCAI, the 

results of the investigations showed that 

there was a production defect in the 

HSECU, which could have contributed 

to the cause of the event. An airplane 

lost pitch control, which resulted in the 

unsafe condition determination that led 

to the issuance of the MCAI. We concur 

with the unsafe condition stated in the 

MCAI. We have not changed this final 

rule in this regard. 

Revisions to Service Information 

Since we issued the NPRM (78 FR 

40065, July 3, 2013), Dassault Aviation 

issued Chapter 5–40–00, Airworthiness 

Limitations, DGT 107838, Revision 3, 

dated July 16, 2012, of the Dassault 

Falcon 7X Maintenance Manual (MM); 

and Dassault Falcon 7X Airplane Flight 

Manual (AFM), DGT105608, Revision 

18, dated November 15, 2013. These 

documents contain no substantive 

changes to the requirements of this final 

rule beyond the procedures specified in 

the revisions of the documents cited in 

the NPRM. We have determined that 

these new procedures will not impose 

an additional burden on any operator. 

This final rule has been changed to refer 

to this revised MM and AFM as the 

appropriate sources of information to 

address the identified unsafe condition. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

We have become aware that some 

operators have misunderstood or 

misinterpreted the Airworthy Product 

paragraph to allow the owner/operator 

to use messages provided by the 

manufacturer as approval of deviations 

during the accomplishment of an ADmandated action. The Airworthy 

Product paragraph does not approve 

messages or other information provided 

by the manufacturer for deviations to 

the requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, the European Aviation 

Safety Agency (EASA), or Dassault 

Aviation’s EASA Design Organization 

Approval (DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

AD. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

40065, July 3, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 40065, 

July 3, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 30 

airplanes of U.S. registry. 

The actions that were required by AD 

2011–16–01, Amendment 39–16759 (76 

FR 47424, August 5, 2011), that are 

retained in this AD take about 340 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

actions that were required by AD 2011– 

16–01 is $28,900 per product. 

We also estimate that it will take 

about 11 work-hours per product to 

comply with the new basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. Based 

on these figures, we estimate the cost of 

this AD on U.S. operators to be $28,050, 

or $935 per product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

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Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations 52547 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0464; or in 

person at the Docket Operations office 

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

through Friday, except Federal holidays. 

The AD docket contains this AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2011–16–01, Amendment 39–16759 (76 

FR 47424, August 5, 2011), and adding 

the following new AD: 

2014–16–23 Dassault Aviation: 

Amendment 39–17947. Docket No. 

FAA–2013–0464; Directorate Identifier 

2012–NM–010–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 9, 2014. 

(b) Affected ADs 

This AD replaces AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). 

(c) Applicability 

This AD applies to all Dassault Aviation 

Model FALCON 7X airplanes, certificated in 

any category, all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by an uncontrolled 

pitch trim runaway during descent. We are 

issuing this AD to prevent an uncontrolled 

pitch trim runaway, which could result in 

loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). Before further flight, do the 

applicable actions specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD. 

(1) For airplanes on which Dassault 

Mandatory Service Bulletin 7X–211, Revision 

1, dated June 14, 2011, has not been done as 

of August 22, 2011 (the effective date of AD 

2011–16–01, Amendment 39–16759 (76 FR 

47424, August 5, 2011)): Modify the airplane 

by adding an automatic reversion logic and 

a means for the pilot to override pitch trim 

control normal modes, and install placards in 

the cockpit in full view of the pilots, in 

accordance with paragraph 2., 

‘‘Accomplishment Instructions for Aircraft 

which have not Already Implemented the 

Revision 1 of the Service Bulletin,’’ of 

Dassault Mandatory Service Bulletin 7X–211, 

Revision 2, dated June 22, 2011, including 

New Standard Installation Checklist and 

Appendix A, and including FCS Data 

Loading Procedure, Issue D, dated May 28, 

2010. 

(2) For airplanes on which Dassault 

Mandatory Service Bulletin 7X–211, Revision 

1, dated June 14, 2011, has been done as of 

August 22, 2011 (the effective date of AD 

2011–16–01, Amendment 39–16759 (76 FR 

47424, August 5, 2011)): Replace the frame of 

the emergency switch box, in accordance 

with paragraph 3., ‘‘Accomplishment 

Instructions for Aircraft which have Already 

Implemented Revision 1 of this Service 

Bulletin,’’ of Dassault Mandatory Service 

Bulletin 7X–211, Revision 2, dated June 22, 

2011, including New Standard Installation 

Checklist and Appendix A, and including 

FCS Data Loading Procedure, Issue D, dated 

May 28, 2010. 

(3) For airplanes equipped with any 

horizontal stabilizer electronic control unit 

(HSECU) part number (P/N) 051244–04, 

replace the HSECU with any HSECU 

identified in paragraph (g)(3)(i), (g)(3)(ii), or 

(g)(3)(iii) of this AD, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–212, Revision 

2, dated July 7, 2011. 

(i) HSECU P/N 051244–02. 

(ii) Verified HSECU P/N 051244–04 having 

a stamped ‘‘V.’’ 

(iii) HSECU P/N 051244–05. 

(h) Retained Credit for Previous Actions 

This paragraph restates the provisions 

specified in paragraph (h) of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). This paragraph provides credit for 

the HSECU replacement required by 

paragraph (g)(3)(i) or (g)(3)(ii) of this AD, if 

those replacements were performed before 

August 22, 2011 (the effective date of AD 

2011–16–01), using Dassault Mandatory 

Service Bulletin 7X–212, Revision 1, dated 

June 23, 2011, which is not incorporated by 

reference in this AD. 

(i) Retained Revision of Airplane Flight 

Manual (AFM) 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–16–01, Amendment 

39–16759 (76 FR 47424, August 5, 2011). As 

of August 22, 2011 (the effective date AD 

2011–16–01), operate the airplane according 

to the limitations and procedures in the 

Dassault Falcon 7X AFM, Revision 12, dated 

June 16, 2011, until the actions required by 

paragraph (p) of this AD are accomplished. 

Revision 12 introduces revised operational 

speed limitations and revised procedures 

accounting for the new TRIM EMERG button. 

(j) Retained Electronic Checklist Database 

Installation 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–16–01, Amendment 

39–16759 (76 FR 47424, August 5, 2011). 

Before further flight, install the electronic 

checklist V0007 database, in accordance with 

the Accomplishment Instructions of Dassault 

Service Bulletin 7X–213, dated June 22, 

2011. Accomplishing the actions required by 

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52548 Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations 

paragraph (o) of this AD terminates the 

actions required by paragraph (j) of this AD. 

(k) Retained Operating Restrictions 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). Before further flight, revise the 

Limitations section of the Dassault Falcon 7X 

AFM to include the information provided in 

figure 1 to paragraph (k) of this AD. This may 

be accomplished by inserting a copy of figure 

1 to paragraph (k) of this AD into the AFM. 

Accomplishment of the actions required in 

paragraph (p) of this AD terminates the 

actions required by paragraph (k) of this AD. 

Figure 1 to Paragraph (k) of this AD— 

Retained AFM Revision 

(l) Retained Maintenance Program Revision 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–16–01, Amendment 

39–16759 (76 FR 47424, August 5, 2011). 

(1) Within 30 days after August 22, 2011 

(the effective date of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011)): Revise the maintenance program to 

incorporate Maintenance Planning Document 

(MPD) Task 27–40–00–710–801, as specified 

in Dassault Aviation, Falcon 7X Maintenance 

Manual (MM), Falcon 7X—Chapter 5–40–00 

after Rev 01, dated June 10, 2011 (commonly 

referred to as Dassault Change Proposal (CP) 

CP009 to Chapter 5–40–00 of Dassault Falcon 

7X MM). The initial compliance time for 

doing the operational test of the HSTS 

electric motors reversion relays is 1,850 flight 

hours after accomplishment of the applicable 

actions required by paragraph (g) of this AD. 

Accomplishment of the actions required in 

paragraph (q) of this AD terminates the 

actions required by paragraph (l) of this AD. 

(2) The MM revision required by paragraph 

(l) of this AD may be done by inserting a 

copy of Maintenance Planning Document 

(MPD) Task 27–40–00–710–801, as specified 

in Dassault Aviation, Falcon 7X Maintenance 

Manual (MM), Falcon 7X—Chapter 5–40–00 

after Rev 01, dated June 10, 2011 (commonly 

referred to as Dassault Change Proposal (CP) 

CP009 to Chapter 5–40–00 of Dassault Falcon 

7X MM), into the MM. When Dassault CP 

CP009 has been included in general revisions 

of the MM, the general revisions may be 

inserted into the MM, provided the relevant 

information in the general revision is 

identical to that in Dassault CP CP009, and 

Dassault CP CP009 may be removed. 

(m) Retained Limitations for Alternative 

Procedures or Intervals 

This paragraph restates the requirements of 

paragraph (m) of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). After the maintenance program has 

been revised as required by paragraph (l) of 

this AD, no alternative procedure or interval 

for the operational test may be used unless 

the procedure and/or interval is approved as 

an alternative method of compliance (AMOC) 

in accordance with the procedures specified 

in paragraph (s) of this AD. 

(n) Retained FAA AD Differences 

This paragraph restates the AD differences 

identified in Note 3 of AD 2011–16–01, 

Amendment 39–16759 (76 FR 47424, August 

5, 2011). This AD differs from the mandatory 

continuing airworthiness information (MCAI) 

and/or service information as follows: 

(1) European Aviation Safety Agency 

(EASA) AD 2011–0114R2, dated July 7, 2011, 

requires repetitive operational tests of the 

HSTS electric motors reversion relays, and 

specifies that the aircraft maintenance 

program may be revised in lieu of those 

repetitive tests. This FAA AD mandates 

revising the maintenance program. 

(2) EASA AD 2011–0114R2, dated July 7, 

2011, does not include any requirement to 

revise the electronic checklist. Paragraph (j) 

of this FAA AD requires this action. 

(3) EASA AD 2011–0114R2, dated July 7, 

2011, mandates amending the minimum 

equipment list (MEL) by removing certain 

items. This FAA AD instead requires revising 

the AFM to prohibit dispatch with those 

items inoperative. The operational effect, 

however, is the same. 

(o) New Fly-By-Wire System Modification 

Within 12 months after accomplishing the 

actions required by paragraph (g) of this AD, 

or within 9 months after the effective date of 

this AD, whichever is later: Modify the flyby-wire system installed in the airplane to 

the 2.1.7.3 standard, in accordance with the 

Accomplishment Instructions of Dassault 

Service Bulletin 7X–214, dated August 30, 

2011, as revised by Dassault Service Bulletin 

7X–214, Erratum, dated January 26, 2012. 

Accomplishment of the actions required in 

paragraph (o) of this AD terminates the 

actions required by paragraph (j) of this AD. 

(p) New AFM Revision 

After accomplishing the actions required 

by paragraph (o) of this AD: Operate the 

airplane thereafter according to the 

limitations and procedures specified in 

Dassault Falcon 7X AFM, DGT105608, 

Revision 18, dated November 15, 2013. 

Accomplishment of the actions required by 

this paragraph terminates the requirements of 

paragraphs (i) and (k) of this AD; after those 

actions have been done, the AFM limitation 

required by paragraph (k) of this AD may be 

removed from the AFM. 

(q) New Maintenance Program Revision 

Within 30 days after the effective date of 

this AD: Revise the maintenance program to 

incorporate Chapter 5–40–00, Airworthiness 

Limitations, DGT 107838, Revision 3, dated 

July 16, 2012, of the Dassault Falcon 7X 

Maintenance Manual (MM), into the MM. 

(1) The initial compliance time for the 

operational test of the HSTS trim emergency 

command is within 650 flight hours after the 

modification required by paragraph (o) of this 

AD. 


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Federal Register / Vol. 79, No. 171 / Thursday, September 4, 2014 / Rules and Regulations 52549 

1 In a January 25, 2013 final rule document (78 

FR 8362), the Commission announced that it would 

add ranges to the Rule for space-constrained 

products and small-duct, high-velocity systems. 

(2) The initial compliance time for the 

operational test of the HSTS electric motors 

reversion relays is within 5,050 flight hours 

after the modification required by paragraph 

(o) of this AD. 

(3) Accomplishment of the actions required 

in paragraph (q) of this AD terminates the 

actions required by paragraph (l) of this AD. 

(r) New Limitations for Alternative Actions 

or Intervals 

After accomplishing the revision required 

by paragraph (q) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (s) of 

this AD. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for AD 

2011–16–01, Amendment 39–16759 (76 FR 

47424, August 5, 2011), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Dassault Aviation’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(t) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0241, dated December 19, 

2011. You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0464-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (u)(5) and (u)(6) of this AD. 

(u) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 9, 2014. 

(i) Chapter 5–40–00, Airworthiness 

Limitations, DGT 107838, Revision 3, dated 

July 16, 2012, of the Dassault Falcon 7X 

Maintenance Manual (MM). 

(ii) Dassault Falcon 7X Airplane Flight 

Manual, DGT105608, Revision 18, dated 

November 15, 2013. The document revision 

level is identified only on the title page and 

page 1 of the List of Effective Sub-SubSections. The document date can only be 

found on the title page. 

(iii) Dassault Service Bulletin 7X–214, 

dated August 30, 2011. 

(iv) Dassault Service Bulletin 7X–214, 

Erratum, dated January 26, 2012. ‘‘Erratum’’ 

appears only in the list of effective/modified 

pages of this document. 

(4) The following service information was 

approved for IBR on August 22, 2011 (76 FR 

47424, August 5, 2011). 

(i) Dassault Aviation, Falcon 7X 

Maintenance Manual, Falcon 7X—Chapter 5– 

40–00 after Rev 01, dated June 10, 2011 

(Commonly referred to as Dassault Change 

Proposal (CP) CP009 to Chapter 5–40–00 of 

Dassault Falcon 7X Maintenance Manual). 

(ii) Dassault Falcon 7X Airplane Flight 

Manual, Revision 12, dated June 16, 2011. 

The document date can only be found in the 

List of Revisions section of the Dassault 

Falcon 7X Airplane Flight Manual. 

(iii) Dassault Mandatory Service Bulletin 

7X–211, Revision 2, dated June 22, 2011, 

including FCS Data Loading Procedure, Issue 

D, dated May 28, 2010, and including New 

Standard Installation Checklist and 

Appendix A,. New Standard Installation 

Checklist and Appendix A are not dated or 

identified with a document number. 

(iv) Dassault Mandatory Service Bulletin 

7X–212, Revision 2, dated July 7, 2011. 

(v) Dassault Service Bulletin 7X–213, dated 

June 22, 2011. 

(5) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.com. 

(6) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

7, 2014. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–21037 Filed 9–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

FEDERAL TRADE COMMISSION 

16 CFR Part 305 

RIN 3084–AB03 

Energy Labeling Rule 

AGENCY: Federal Trade Commission. 

ACTION: Final rule; correction. 

SUMMARY: The Federal Trade 

Commission (‘‘Commission’’) is 

correcting a final rule published in the 

Federal Register of August 12, 2014, 

which amends the Energy Labeling Rule 

by updating comparability ranges for 

certain heating and cooling products 

and making conforming changes to the 

Rule’s sample labels. 

DATES: Effective Date: September 4, 

2014. 

FOR FURTHER INFORMATION CONTACT: 

Hampton Newsome, Attorney, Division 

of Enforcement, Bureau of Consumer 

Protection, Federal Trade Commission, 

Washington, DC 20580; (202) 326–2889. 

SUPPLEMENTARY INFORMATION: This 

document corrects tables and sample 

labels for central air conditioners in the 

August 12, 2014, final rule document 

(79 FR 46985) amending the Energy 

Labeling Rule (‘‘Rule’’), 16 CFR part 

305. Specifically, this document 

corrects the lower range numbers for 

several central air conditioner categories 

to reflect new DOE minimum 

conservation standards scheduled for 

January 1, 2015, adds range numbers for 

space-constrained and small-duct, highvelocity product categories omitted from 

the tables in the final rule document,1

and makes conforming corrections to 

the range numbers on the sample labels. 

In FR Doc. 2014–18501, appearing in 

the Federal Register of Tuesday, August 

12, 2014 (79 FR 46985), the following 

corrections are made: 

Appendix H to Part 305 [Corrected] 

■ 1. On page 46986, the table in 

Appendix H to Part 305 is corrected to 

read as follows: 

mstockstill on DSK4VPTVN1PROD with RULES