5034 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 

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. 

(h) Inspection 

If a rudder assembly having any part 

number starting with A55471500 or 

A55471500XXX (where XXX stands for any 

numerical value) is found during the 

inspection required by paragraph (g) of this 

AD, and that rudder assembly has been 

inspected before the effective date of this AD, 

as specified in Airbus Service Bulletin A330– 

55–3038, dated November 7, 2007 (which is 

not incorporated by reference in this AD); or 

Airbus Service Bulletin A340–55–4034, 

dated November 7, 2007 (which is not 

incorporated by reference in this AD); as 

applicable; and that rudder assembly has 

been removed and installed on any airplane 

after the inspection or that has been 

inspected off-wing: Within 3 months after the 

effective date of this AD, do an ultrasonic test 

inspection for damage (e.g., disbonding and 

liquid ingress) of the rudder side panel along 

the Z-profile and in the booster area, in 

accordance with Airbus AOT A55L001–12, 

dated December 20, 2012. If any damage is 

found, before further flight, do the 

inspections specified in paragraphs (h)(1) 

and (h)(2) of this AD to confirm disbonding 

damage, in accordance with Airbus AOT 

A55L001–12, dated December 20, 2012. 

(1) Do an elasticity of laminate checker 

inspection to detect external and internal 

disbonding. 

(2) Do a woodpecker or tap test inspection 

to detect external disbonding. 

(i) Repair 

If any disbonding or damage (e.g. liquid 

ingress) is confirmed during any inspection 

required by paragraphs (h), (h)(1), and (h)(2) 

of this AD, repair at the time specified in 

paragraph (i)(1), (i)(2), or (i)(3) of this AD, as 

applicable. 

(1) If the disbonding is less than or equal 

to 50 millimeters (mm) in width and less 

than or equal to 150 mm in length: Before 

further flight, vent the rudder core using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. Within 100 flight cycles 

after venting the rudder core, do a permanent 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval for the venting and 

repair methods must include the DOAauthorized signature. 

(2) If the disbonding is greater than 50 mm 

in width, or greater than 150 mm in length: 

Before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or Airbus’s EASA 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(3) If any damage other than disbonding 

(e.g., liquid ingress) is confirmed during any 

inspection required by paragraph (h) of this 

AD, before further flight, repair, using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(j) Parts Installation Limitation 

As of the effective date of this AD, you may 

install, on any airplane, a rudder assembly 

having part number A55471500XXX (where 

XXX stands for any numerical value), 

provided the inspection required by 

paragraph (h) of this AD and all applicable 

repair actions required by paragraph (i) of 

this AD are done before further flight. 

(k) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0270R1, dated 

November 27, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0525. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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) Airbus Alert Operators Transmission 

A55L001–12, dated December 20, 2012, 

including Inspection Flow Chart AOpT ref.: 

A55L001–12, not dated. The document 

number and date of this document are 

identified on only the first page of this AOT. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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 January 

15, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–01184 Filed 1–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0527; Directorate 

Identifier 2014–NM–045–AD; Amendment 

39–18071; AD 2015–02–04] 

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 MYSTERE– 

FALCON 50 airplanes. This AD was 

prompted by a report of an untimely 

and intermittent indication of slat 

activity due to chafing of the electrical 

wiring under the glare shield and 

behind the flight deck front panel. This 

AD requires installing two protective 

plates between the electrical wiring 

under the glare shield and the engine 

fire pull handles. We are issuing this AD 

to prevent chafing of the electrical 


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Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 5035 

wiring, which could result in a short 

circuit and generation of smoke in the 

cockpit, potential loss of several 

functions essential for safe flight, and 

consequent reduced controllability of 

the airplane. 

DATES: This AD becomes effective 

March 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 6, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov/#!docketDetail;

D=FAA-2014-0527 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 MYSTERE–FALCON 50 

airplanes. The NPRM published in the 

Federal Register on August 12, 2014 (79 

FR 47031). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0024, dated January 23, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on certain Dassault 

Aviation Model MYSTERE–FALCON 50 

airplanes. The MCAI states: 

One operator experienced an untimely and 

intermittent indication of slat activity on his 

aeroplane. The results of the subsequent 

investigation revealed that electrical wiring 

under the glare shield and behind the flight 

deck front panel was chafing with hardware 

and was short-circuited to ground. This 

situation may have resulted from an incorrect 

installation of the wiring during a previous 

maintenance action in the area. A design 

review identified a lack of protection of the 

affected electrical wiring bundle, which 

would have prevented damage caused by 

chafing with aeroplane structural parts. 

This condition, if not corrected, might lead 

to an electrical short circuit and generation 

of smoke, possibly affecting operation of 

systems and resulting in reduced control of 

the aeroplane. 

To address this potential unsafe condition, 

Dassault Aviation issued [service bulletin] SB 

F50–530, providing instructions for 

installation of a protective plate on the 

electrical wiring. 

For the reasons described above, this 

[EASA] AD requires modification of the 

aeroplane by installing a protective plate on 

the electrical wiring. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov/#!documentDetail;

D=FAA-2014-0527-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 47031, August 12, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, with minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

47031, August 12, 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 47031, 

August 12, 2014). 

Related Service Information 

We reviewed Dassault Service 

Bulletin F50–530, dated November 12, 

2013. The service information describes 

procedures for installing two protective 

plates between the electrical wiring 

under the glare shield and the engine 

fire pull handles. You can find this 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0527. 

Costs of Compliance 

We estimate that this AD affects 250 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Installation ....................................................... 26 work-hours × $85 per hour = $2,210 ........ $96 $2,306 $576,500 

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 


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5036 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 

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-2014-0527; 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): 

2014–02–04 Dassault Aviation: 

Amendment 39–18071. Docket No. 

FAA–2014–0527; Directorate Identifier 

2014–NM–045–AD. 

(a) Effective Date 

This AD becomes effective March 6, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dassault Aviation 

Model MYSTERE–FALCON 50 airplanes, 

certificated in any category, as identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Airplanes with manufacturer serial 

numbers 5, 7, 27, 30, 34, 36, 78, 132, and 251 

through 352 inclusive. 

(2) Airplanes with manufacturer serial 

numbers 2 through 250 inclusive, having 

Honeywell (formerly Allied Signal, Garrett 

AiResearch) TFE731–40–1C engines 

modified by Dassault Aviation Service 

Bulletin F50–280. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by a report of an 

untimely and intermittent indication of slat 

activity due to chafing of the electrical wiring 

under the glare shield and behind the flight 

deck front panel. We are issuing this AD to 

prevent chafing of the electrical wiring, 

which could result in a short circuit and 

generation of smoke in the cockpit, potential 

loss of several functions essential for safe 

flight, and consequent reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Install Protective Plates 

Within 74 months after the effective date 

of this AD, install two Rilsan protective 

plates between the glare shield electrical 

wiring and the engine fire pull handles, in 

accordance with the Accomplishment 

Instructions of Dassault Service Bulletin 

F50–530, dated November 12, 2013. 

(h) 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. 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 Dassault Aviation’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0024, dated 

January 23, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating it in Docket No. 

FAA–2014–0527–0002. 

(j) 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) Dassault Service Bulletin F50–530, 

dated November 12, 2013. 

(ii) Reserved. 

(3) 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. 

(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 January 

12, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–01185 Filed 1–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30998; Amdt. No. 3626] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule amends, suspends, 

or removes Standard Instrument 

Approach Procedures (SIAPs) and 

associated Takeoff Minimums and 

Obstacle Departure Procedures for 

operations at certain airports. These 

regulatory actions are needed because of 

the adoption of new or revised criteria, 

or because of changes occurring in the 

National Airspace System, such as the 

commissioning of new navigational 

facilities, adding new obstacles, or 

changing air traffic requirements. These 


rljohnson on DSK4SPTVN1PROD with RULES