Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 43613 

Instructions of Boeing Alert Service Bulletin 

747–53A2866, dated December 4, 2013, 

except as provided by paragraph (h) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the applicable inspection of the 

forward and aft tension tie channels 

thereafter at the applicable time and intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2866, 

dated December 4, 2013. 

(1) At each tension tie station from 880 to 

1100: Do a detailed inspection for cracks in 

the forward and aft tension tie channels. 

(2) At each tension tie station from 880 to 

1100: Do a detailed inspection for cracks in 

the forward and aft tension tie channels, and 

do a surface HFEC inspection for cracks 

around fasteners in the tension tie channels. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(l) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@faa.gov. 

(m) 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. 

(i) Boeing Alert Service Bulletin 747– 

53A2866, dated December 4, 2013, 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) 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. 

(5) 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 July 13, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–17312 Filed 7–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0055; Directorate 

Identifier 2013–NM–167–AD; Amendment 

39–17907; AD 2014–15–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A310–304, –322, –324, 

and –325 airplanes. This AD was 

prompted by reports of insufficient 

clearance between the fuel quantity 

indicator (FQI) probes and the adjacent 

structure and metallic components in 

the wing fuel tanks. This AD requires a 

one-time detailed visual inspection for 

sufficient clearance between FQI probes 

on both the left-hand side and righthand side of the trim horizontal 

stabilizer and the adjacent structure and 

metallic components in the fuel tanks, 

and modification if necessary. We are 

issuing this AD to detect and correct 

insufficient clearance, which could lead 

to electrical arcing in a fuel tank during 

a lightning strike, which could result in 

ignition and consequent fire or 

explosion in the fuel tank. 

DATES: This AD becomes effective 

September 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 2, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0055; or in 

person at the Docket Management 

Facility, 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 Airbus SAS, 

Airworthiness Office—EAW, 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 http://www.airbus.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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A310– 

304, –322, –324, and –325 airplanes. 

The NPRM published in the Federal 

Register on February 25, 2014 (79 FR 

10431). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0188, 

dated August 19, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information to correct an 

unsafe condition on certain Airbus 


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43614 Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 

Model A310–304, –322, –324, and –325 

airplanes. The MCAI states: 

Airbus investigations on A300 aeroplanes 

revealed insufficient clearance between the 

Fuel Quantity Indicator (FQI) probes and 

adjacent structure or metallic components in 

the wing fuel tanks. A300–600 and A310 

aeroplanes are also affected as they are 

identical in design. 

This condition, if not detected and 

corrected, could lead to electric arcing in a 

fuel tank in case of lightning strike, which 

could result in ignition and consequent fire 

or explosion in the fuel tank. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A300– 

28–0080, SB A300–28–6065 and SB A310– 

28–2145 and DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civil] France issued [an] AD * * * 

to cover A300 aeroplanes and [an] AD * * * 

to cover A300–600 and A310 aeroplanes 

(both EASA ADs were later revised). [Both 

EASA ADs correspond to FAA AD 2004–05– 

05, Amendment 39–13499 (69 FR 10319, 

dated March 5, 2004)]. 

Since those [EASA] ADs were issued, 

further analysis showed that they do not 

cover all potentially affected aeroplanes: 

A310 aeroplanes with optional Mod. no. 

12248 embodied were excluded from the 

applicability of [a] DGAC France AD * * * 

but are potentially affected, and therefore 

addressed through this [EASA] AD. 

For the reasons described above, this 

[EASA] AD requires a one-time [detailed 

visual] inspection of the affected aeroplanes 

for sufficient clearance between FQI probes 

[on both the left-hand (LH) side and righthand (RH) side of the trim horizontal 

stabilizer] and adjacent structure/metallic 

parts and, depending on findings, 

modification of the FQI probes. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0055- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 10431, February 25, 2014) or on the 

determination of the cost to the public. 

‘‘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. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (79 FR 10431, February 

25, 2014), we proposed to prevent the 

use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (79 FR 10431, February 25, 2014) 

about these proposed changes. However, 

a comment was provided for another 

NPRM, Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013), in which the commenter stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that 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 action must be accomplished using 

a method approved by the FAA, the 

European Aviation Safety Agency 

(EASA), or Airbus’s EASA 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. 

Other commenters to the NPRM 

discussed previously, Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), pointed out 

that in many cases the foreign 

manufacturer’s service bulletin and the 

foreign authority’s MCAI might have 

been issued some time before the FAA 

AD. Therefore, the DOA might have 

provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 


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Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 43615 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. We also 

have decided not to include a generic 

reference to either the ‘‘delegated agent’’ 

or ‘‘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 in the 

Contacting the Manufacturer paragraph 

of this AD. 

Conclusion 

We reviewed the relevant data 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 minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

10431, February 25, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 10431, 

February 25, 2014). 

Costs of Compliance 

We estimate that this AD affects 2 

airplanes of U.S. registry. 

We also estimate that it will take 

about 8 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

$0 per product. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $1,360, or $680 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 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-2014-0055; or in 

person at the Docket Management 

Facility 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 adding 

the following new airworthiness 

directive (AD): 

2014–15–05 Airbus: Amendment 39–17907. 

Docket No. FAA–2014–0055; Directorate 

Identifier 2013–NM–167–AD. 

(a) Effective Date 

This AD becomes effective September 2, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A310– 

304, –322, –324, and –325 airplanes, 

certificated in any category, on which Airbus 

Modification Number 12248 has been 

embodied. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by reports of 

insufficient clearance between the fuel 

quantity indicator (FQI) probes and the 

adjacent structure and metallic components 

in the wing fuel tanks. We are issuing this 

AD to detect and correct insufficient 

clearance, which could lead to electrical 

arcing in a fuel tank during a lightning strike, 

which could result in ignition and 

consequent fire or explosion in the fuel tank. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Modification 

Within 30 months after the effective date 

of this AD, do a one-time detailed visual 

inspection for clearance between the FQI 

probes located in the trimmable horizontal 

stabilizer tank and the adjacent structure and 

metallic components, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–28–2145, Revision 01, 

dated March 4, 2003. 

(1) If the clearance of an FQI probe is found 

to be 3.0 millimeters (mm) (0.118 inch) or 

more: No further action is required by 

paragraph (g) of this AD. 

(2) If the clearance of an FQI probe is found 

to be 2.5 mm (0.98 inch) or more, and less 

than 3.0 mm (0.118 inch): Before further 

flight, loosen the probe screws and move the 

probe up and down to get the required 

minimum gap of 3.0 mm (0.118 inch), in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

28–2145, Revision 01, dated March 4, 2003. 

(3) If the clearance of an FQI probe is found 

to be less than 2.5 mm (0.118 inch): Before 

further flight, modify each affected FQI probe 

by installing new FQI probe supports, in 

accordance with Step 3.C., ‘‘Repair,’’ of the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–28–2145, Revision 01, 

dated March 4, 2003. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A310–28–2145, dated August 21, 

2001, which is not incorporated by reference 

in this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 


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43616 Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 

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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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. 

(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 Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0188, dated August 19, 2013, 

for related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0055-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (k)(3) and (k)(4) of this AD. 

(k) 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. 

(i) Airbus Service Bulletin A310–28–2145, 

Revision 01, dated March 4, 2003. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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 http://www.airbus.com. 

(4) 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. 

(5) 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 July 13, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–17313 Filed 7–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0177; Directorate 

Identifier 2013–NM–189–AD; Amendment 

39–17912; AD 2014–15–10] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 7X 

airplanes. This AD was prompted by a 

report of a crew alerting system message 

caused by an inversion of the wiring in 

the slats control manifold (SCM). This 

AD requires an operational test of the 

SCM, and replacing the affected SCM 

with a serviceable SCM if necessary. We 

are issuing this AD to detect and correct 

inversion of the wiring in the SCM, 

which could lead to a commanded 

retraction of the median and outboard 

slats in flight, and result in reduced 

controllability of the airplane. 

DATES: This AD becomes effective 

September 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 2, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0177; or in 

person at the Docket Management 

Facility, 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 by adding an AD that would 

apply to certain Dassault Aviation 

Model FALCON 7X airplanes. The 

NPRM published in the Federal 

Register on April 4, 2014 (79 FR 18846). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0195, 

dated August 27, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Dassault Aviation Model 

FALCON 7X airplanes. The MCAI 

states: 

During a ferry flight, the crew of a Falcon 

7X aeroplane reported a Crew Alerting 

System Message ‘‘FCS—SLATS INB EXTEND 

FAIL’’ with associated fault code and root 

cause: ‘‘FCS SEC FCS fault/SFCI3 fault’’. The 

crew applied the applicable Aircraft Flight 

Manual procedure and the aeroplane landed 

uneventfully. 

The results of the manufacturer technical 

investigations concluded that the cause of 

this event was an inversion of the wiring in 

the slats control manifold (SCM). 

This condition, if not detected and 

corrected, could lead to un-commanded 

retraction of the median and outboard slats 

in flight, resulting in reduced control of the 

aeroplane. 

To address this potential unsafe condition, 

Dassault Aviation issued Service Bulletin 

(SB) F7X–244, with instructions for an 

operational test of the SCM. 

For the reasons described above, this 

[EASA] AD requires an operational test of the 

SCM and, depending on findings, 

accomplishment of the applicable corrective 

actions [replacing the affected SCM with a 

serviceable SCM if necessary]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0177- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 


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