5032 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 

(ii) Airbus A300–600 Variation 

0CVLG120001/C0S, dated August 24, 2012, 

to Airbus A300–600 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

April 18, 2012. 

(iii) Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

November 30, 2012. 

(4) The following service information was 

approved for IBR on April 28, 2009 (74 FR 

12228, March 24, 2009). 

(i) Airbus A300–600 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006. 

(ii) Airbus A310 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 21, 2006. 

(5) 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. 

(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 January 

13, 2015. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–01182 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–2014–0525; Directorate 

Identifier 2013–NM–235–AD; Amendment 

39–18078; AD 2015–02–11] 

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 A330–300, A340–200, 

and A340–300 series airplanes. This AD 

was prompted by a report of substantial 

inner skin disbonding damage found on 

a rudder. This AD requires performing 

an inspection for damage of certain 

rudders, and repair if necessary. We are 

issuing this AD to detect and correct 

damage of the rudder, which could 

result in reduced structural integrity of 

the rudder. 

DATES: This AD becomes effective 

March 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications 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-2014-0525; 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—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. 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: 

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. 

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 A330– 

300, A340–200, and A340–300 series 

airplanes. The NPRM published in the 

Federal Register on August 13, 2014 (79 

FR 47387). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0270R1, dated 

November 27, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for Airbus Model A330–300, A340–200, 

and A340–300 series airplanes. The 

MCAI states: 

One A310 operator found substantial inner 

skin disbonding damage on a rudder. The 

results of the subsequent investigation 

revealed that the most probable cause of this 

damage was a blunt impact with no visible 

damage from outside during the rudder 

handling. Such type of damage might grow 

with pressure variation during ground-airground cycles, and tests performed with 

other rudders showed a rapid propagation of 

damage during artificial pressure cycling. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder. 

For the affected A310 and A300–600 

aeroplanes, EASA issued AD 2013–0039 

[http://ad.easa.europa.eu/blob/easa_ad_

2013_0039.pdf/AD_2013-0039], to address 

and correct this potential unsafe condition. 

As potentially affected rudders can also be 

installed on A330 and A340 aeroplanes, 

Airbus issued Alert Operator Transmission 

(AOT) A55L001–12 [dated December 20, 

2012], pending Aircraft Maintenance Manual 

(AMM) 27–21–41 PB401 revision, to provide 

operators with updated rudder handling 

procedures. 

EASA issued AD 2013–0270 [http://

ad.easa.europa.eu/blob/easa_ad_2013_

0270.pdf/AD_2013-0270], to require 

identification of affected rudders P/N [part 

number] A55471500XXX (where XXX stands 

for any numerical value), a one-time 

ultrasonic test (UT) inspection of each 

affected rudder to detect signs of disbonding 

and, depending on findings, accomplishment 

of applicable corrective action(s). 

After [EASA] AD 2013–0270 was issued, 

operators commented that the batch of 

rudders to be inspected was not correctly 

defined. 

For the reason described above, [EASA] AD 

2013–0270 is revised to clarify that no action 

is required for rudders previously inspected 

in accordance with Airbus Service Bulletin 

(ASB) A330–55–3038 or SB A340–55–4034 

[which are required by FAA AD 2009–10–11, 

Amendment 39–15907 (74 FR 23622, May 20, 

2009)], as applicable to aeroplane model, 

provided the rudder has never been removed 

and/or installed on an aeroplane since this 

inspection. 

Required actions include an elasticity 

of laminate checker inspection of the 

rudder side panel to detect external and 

internal disbonding, and a woodpecker 

or tap test inspection to detect external 

disbonding, and repair if necessary. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0525- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 47387, 

August 13, 2014) and the FAA’s 

response. 

Request To Correct Certain Document 

Numbers 

Lufthansa Technik (Lufthansa) asked 

that we correct certain document 


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Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 5033 

numbers for the service information 

identified in paragraph (h) of the NPRM 

(79 FR 47387, August 13, 2014). 

Lufthansa stated that paragraph (h) of 

the NPRM incorrectly refers to Airbus 

Service Bulletins A300–55–3038 and 

A310–55–4034, instead of Airbus 

Service Bulletins A330–55–3038 and 

A340–55–4034, both dated November 7, 

2007. 

We agree with the commenter for the 

reason provided. We have corrected the 

document numbers for the service 

information identified in paragraph (h) 

of this AD accordingly. 

Compliance Time Change 

We revised the compliance time in 

paragraph (g) of this AD for the part 

numbers and serial numbers that cannot 

be identified from ‘‘before further flight’’ 

to ‘‘within 3 months after the effective 

date of this AD.’’ We have also revised 

the compliance time in paragraph (h) of 

this AD for the ultrasonic test inspection 

from ‘‘before further flight’’ to ‘‘within 

3 months after the effective date of this 

AD.’’ This compliance time corresponds 

to the compliance time specified in the 

MCAI. We have determined this 

compliance time will provide an 

acceptable level of safety. 

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 minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

47387, August 13, 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 47387, 

August 13, 2014). 

Related Service Information 

Airbus has issued Alert Operators 

Transmission A55L001–12, dated 

December 20, 2012. The service 

information describes procedures for an 

inspection for damage of certain 

rudders. You can find this information 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0525. 

Costs of Compliance 

We estimate that this AD affects 74 

airplanes of U.S. registry. 

We also estimate that it will take 

about 12 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 

about $0 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $75,480, or 

$1,020 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in 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 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-2014-0525; 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): 

2015–02–11 Airbus: Amendment 39–18078. 

Docket No. FAA–2014–0525; Directorate 

Identifier 2013–NM–235–AD. 

(a) Effective Date 

This AD becomes effective March 6, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; except 

airplanes on which Airbus Modification 

41800 has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Reason 

This AD was prompted by a report of 

substantial inner skin disbonding damage on 

a rudder. We are issuing this AD to detect 

and correct damage of the rudder, which 

could result in reduced structural integrity of 

the rudder. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Rudder Assembly Identification 

Within 3 months after the effective date of 

this AD, inspect for the rudder assembly part 

number and serial number, in accordance 

with Airbus Alert Operators Transmission 

(AOT) A55L001–12, dated December 20, 

2012. If the part number or serial number 

cannot be identified, within 3 months after 

the effective date of this AD, identify the part 

number and serial number using a method 


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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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