71304 Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 5341, Fuselage, Wing Attach Fittings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

structural failure of the attachment of the 

wing to the fuselage that resulted from failed 

lateral fuselage tie rods. We are issuing this 

AD to correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraphs (g) 

through (h) of this AD, unless already done. 

(g) Determine Date of Installation or Date of 

Last Replacement of the Lateral Fuselage Tie 

Rods and Attaching Nuts 

Within the next 30 days after January 6, 

2015 (the effective date of this AD), review 

the aircraft records to determine the date of 

installation or date of last replacement of the 

lateral fuselage tie rods and attaching nuts. 

(h) Replace the Lateral Fuselage Tie Rod and 

Attaching Nuts 

Initially replace the lateral fuselage tie rod 

and attaching nuts at whichever of the 

compliance times specified in paragraph 

(h)(1) or paragraph (h)(2) of this AD that 

applies. Repetitively thereafter replace the 

lateral fuselage tie rod and attaching nuts 

every 2,000 hours TIS or 18 years, whichever 

occurs first. Do the replacement following the 

procedures in paragraph 2.C. of the 

Accomplishment Instructions and the table 

on Figure 1 in British Aerospace Military 

Aircraft and Aerostructures BAe Aircraft 

Bulletin for De Havilland Moth Aircraft, 

Document Type and Ref No Technical News 

Sheet CT (Moth) No 29, Issue 3, dated March 

1, 1999. 

(1) If the date of lateral fuselage tie rod 

installation or date of last replacement is 

known: Do the initial replacement at 

whichever of the following compliance times 

in paragraph (h)(1)(i) or paragraph (h)(1)(ii) of 

this AD that occurs later: 

(i) Upon accumulating 2,000 hours TIS on 

the lateral fuselage tie rod or upon reaching 

18 years from the last lateral fuselage tie rod 

replacement, whichever occurs first; or 

(ii) Within the next 6 months after January 

6, 2015 (the effective date of this AD) or 

within the next 100 hours TIS January 6, 

2015 (after the effective date of this AD), 

whichever occurs first. 

(2) If the date of lateral fuselage tie rod 

installation or date of last replacement is not 

known: Do the initial replacement within the 

next 6 months after January 6, 2015 (the 

effective date of this AD) or within the next 

100 hours TIS after January 6, 2015 (the 

effective date of this AD), whichever occurs 

first. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager of the Fort Worth 

Airplane Certification Office (ACO), the 

Manager of the Los Angeles Aircraft 

Certification Office (ACO), and the Manager 

of the Standards Office, FAA, have the 

authority to approve AMOCs for their 

respective products covered by 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 applicable FAA office, 

send it to the attention of the person 

identified in paragraphs (j)(1), (j)(2), or (j)(3), 

as applicable. 

(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. 

(j) Related Information 

(1) For more information about this AD for 

airplanes covered under Type Certificate 

Data Sheet (TCDS) A5PC (Model de 

Havilland DH 82A airplanes built in 

Australia), contact Andrew McAnaul, 

Aerospace Engineer, FAA, Fort Worth ACO, 

ASW–150 (c/o San Antonio MIDO), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; phone: (210) 308–3365; fax: 

(210) 308–3370; email: andrew.mcanaul@

faa.gov. 

(2) For more information about this AD for 

airplanes covered under TCDS A8EU (Model 

de Havilland DH 82A airplanes built in the 

United Kingdom), contact Fred Guerin, 

Aerospace Engineer, FAA, Los Angeles ACO, 

3960 Paramount Blvd., Suite 100, Lakewood, 

California 90712; phone (562) 627–5232; fax: 

(562) 627–5210; email: fred.guerin@faa.gov. 

(3) For more information about this AD for 

airplanes covered under TCDS 2–439 (Model 

de Havilland DH 83 airplanes built in the 

United Kingdom), contact Karl Schletzbaum, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329– 

4123; fax: (816) 329–4090; email: 

karl.schletzbaum@faa.gov. 

(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 the AD specifies otherwise. 

(i) British Aerospace Military Aircraft and 

Aerostructures BAe Aircraft Bulletin for De 

Havilland Moth Aircraft, Document Type and 

Ref No Technical News Sheet CT (Moth) No 

29, Issue 3, dated March 1, 1999. 

(ii) Reserved. 

(3) For British Aerospace Military Aircraft 

and Aerostructures service information 

identified in this AD, contact: 

(i) For de Havilland DH 82A airplanes: de 

Havilland Support Ltd, Building 213, 

Duxford Airfield, Cambridge, United 

Kingdom CB22 4QR; telephone: +44 (0) 1223 

830090; fax: +44 (0) 1223 830085; email: 

info@dhsupport.com; Internet: http://

www.dhsupport.com/moth.php. 

(ii) For de Havilland DH 83 airplanes: Air 

Stratus Ltd., Oaksey Park Airfield, Oaksey, 

Malmesbury, Wiltshite, United Kingdom SN 

16 9SD; telephone: +44 (0) 1666 575111; no 

known Internet address. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on 

November 18, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–27789 Filed 12–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0776; Directorate 

Identifier 2013–NM–240–AD; Amendment 

39–18033; AD 2014–23–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–20– 

06 for all Airbus Model A340–211, 

–212, –213, –311, –312, –313, –541, and 

–642 airplanes. AD 2013–20–06 

required revising the maintenance 

program to incorporate certain 

maintenance requirements and 

airworthiness limitations. This new AD 

requires revising the maintenance or 

inspection program to incorporate 

certain other maintenance requirements 

and airworthiness limitations. This AD 

was prompted by a determination that 

existing maintenance requirements are 

not adequate to address the aging effects 

of aircraft systems. We are issuing this 

AD to address the aging effects of 

aircraft systems. Such aging effects 

could change the characteristics of 

systems’ life-limited components 

leading to an increased potential for 

failure, which, in isolation or in 

combination with one or more other 

specific failures or events, could result 

in failure of certain life limited parts, 

which could reduce the structural 

integrity or the controllability of the 

airplane. 

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Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 71305 

DATES: This AD becomes effective 

December 17, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 17, 2014. 

We must receive comments on this 

AD by January 16, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0776; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

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 

On September 17, 2013, we issued AD 

2013–20–06, Amendment 39–17612 (78 

FR 64156, October 28, 2013). AD 2013– 

20–06 applied to all Airbus Model 

A340–211, –212, –213, –311, –312, 

–313, –541, and –642 airplanes. AD 

2013–20–06 was prompted by a 

determination that existing maintenance 

requirements were are not adequate to 

address the unsafe condition. AD 2013– 

20–06 required revising the 

maintenance program to incorporate 

certain maintenance requirements and 

airworthiness limitations. We issued AD 

2013–20–06 to address the aging effects 

of aircraft systems. Such aging effects 

could change the characteristics of 

systems life-limited components leading 

to an increased potential for failure, 

which, in isolation or in combination 

with one or more other specific failures 

or events, could result in failure of 

certain life limited parts, which could 

reduce the structural integrity or the 

controllability of the airplane. 

Since we issued AD 2013–20–06, 

Amendment 39–17612 (78 FR 64156, 

October 28, 2013), we determined that 

existing maintenance requirements are 

not adequate to address the aging effects 

of aircraft systems. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0269, 

dated November 7, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

all Airbus Model A340–211, –212, –213, 

–311, –312, –313, –541, and –642 

airplanes. The MCAI states: 

The airworthiness limitations for Airbus 

aeroplanes are currently published in 

Airworthiness Limitations Section (ALS) 

documents. 

The airworthiness limitations applicable to 

the Ageing Systems Maintenance (ASM) are 

given in Airbus A340 ALS Part 4, which is 

approved by EASA. 

Revision 03 of Airbus A340 ALS Part 4 

introduces more restrictive maintenance 

requirements and/or airworthiness 

limitations. Failure to comply with these 

instructions could result in an unsafe 

condition. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0021 (http://ad.easa.europa.eu/ad/ 

2012–0021) [which corresponds to FAA AD 

2013–20–06, Amendment 39–17612 (78 FR 

64156, October 28, 2013)], which is 

superseded, and requires accomplishment of 

the actions specified in Airbus A340 ALS 

Part 4 at Revision 03. 

In addition, this [EASA] AD also 

supersedes EASA AD 2008–0026 (http://

ad.easa.europa.eu/ad/2008–0026) [which 

corresponds to FAA AD 2010–15–02, 

Amendment 39–16368 (75 FR 42589, July 22, 

2010)] and EASA AD 2008–0160 (http://

ad.easa.europa.eu/ad/2008–0160) [which 

corresponds to FAA AD 2009–18–20, 

Amendment 39–16017 (74 FR 46313, 

September 9, 2009)], whose requirements 

applicable to A340 aeroplanes have been 

transferred into Airbus A340 ALS Part 4. 

The unsafe condition is the aging effects 

of aircraft systems. Such aging effects 

could change the characteristics of 

systems’ life-limited components 

leading to an increased potential for 

failure, which, in isolation or in 

combination with one or more other 

specific failures or events, could result 

in failure of certain life limited parts, 

which could reduce the structural 

integrity or the controllability of the 

airplane. You may examine the MCAI 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0776. 

Relevant Service Information 

Airbus has issued A340 

Airworthiness Limitations Section 

(ALS) Part 4—Ageing Systems 

Maintenance, Revision 03, dated 

November 15, 2012. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This AD requires revisions to certain 

operator maintenance documents to 

include new inspections. Compliance 

with these inspections is required by 14 

CFR 91.403(c). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by these 

inspections, the operator may not be 

able to accomplish the inspections 

described in the revisions. In this 

situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance according to paragraph (k) 

of this AD. The request should include 

a description of changes to the required 

inspections that will ensure the 

continued operational safety of the 

airplane. 

There are no products of this type 

currently registered in the United States. 

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71306 Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between This AD and MCAI 

or Service Information 

This AD incorporates Airbus A340 

ALS Part 4—Ageing Systems 

Maintenance, Revision 03, dated 

November 15, 2012, including the 

compliance times for the actions. 

However, the compliance times for 

certain initial actions are different from 

those specified in Airbus A340 ALS Part 

4—Ageing Systems Maintenance, 

Revision 03, dated November 15, 2012, 

because the actions and associated 

compliance times were required by AD 

2009–18–20, Amendment 39–16017 (74 

FR 46313, September 9, 2009). 

Therefore, the initial compliance time 

for these actions is relative to the 

effective date of the applicable 

superseded AD, as specified in 

paragraph (h) of this AD. 

The MCAI specifies that if there are 

findings from the ALS inspection tasks, 

corrective actions must be accomplished 

in accordance with Airbus maintenance 

documentation. However, this AD does 

not include that requirement. Operators 

of U.S.-registered airplanes are required 

by general airworthiness and 

operational regulations to perform 

maintenance using methods that are 

acceptable to the FAA. We consider 

those methods to be adequate to address 

any corrective actions necessitated by 

the findings of ALS inspections required 

by this AD. 

Related Rulemaking 

Certain maintenance requirements 

specified in A340 ALS Part 4—Ageing 

Systems Maintenance, Revision 03, 

dated November 15, 2012, are already 

required by other ADs. Therefore, 

accomplishing the actions required by 

this AD will terminate the requirements 

of the following ADs for Model A340 

airplanes. 

• AD 2003–14–11, Amendment 39– 

13230 (68 FR 41521, July 14, 2003). 

• AD 2004–11–08, Amendment 39– 

13654 (69 FR 31874, June 8, 2004). 

• AD 2004–13–25, Amendment 39– 

13707 (69 FR 41394, July 9, 2004). 

• AD 2004–18–14, Amendment 39– 

13793 (69 FR 55326, September 14, 

2004). 

• AD 2007–05–12, Amendment 39– 

14973 (72 FR 10057, March 7, 2007). 

• AD 2008–06–07, Amendment 39– 

15419 (73 FR 13103, March 12, 2008; 

corrected April 15, 2008 (73 FR 20367)). 

• AD 2012–04–07, Amendment 39– 

16963 (77 FR 12989, March 5, 2012). 

• AD 2009–18–20, Amendment 39– 

16017 (74 FR 46313, September 9, 

2009), which requires the identification 

and modification of certain standard 

spoiler servo-controls; and 

• AD 2010–15–02, Amendment 39– 

16368 (75 FR 42589, July 22, 2010), 

which requires various detailed visual 

inspections for corrosion and wear 

detection of the input gear box and 

down drive shafts of all wing flap tracks 

and corrective actions. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2014–0776; 

Directorate Identifier 2013–NM–240– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 0 

airplanes of U.S. registry. 

We estimate that it will take about 1 

work-hour 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 

$85 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. 

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) 

2013–20–06, Amendment 39–17612 (78 

FR 64156, October 28, 2013), and 

adding the following new AD: 

2014–23–17 Airbus: Amendment 39–18033. 

Docket No. FAA–2014–0776; Directorate 

Identifier 2013–NM–240–AD. 

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Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 71307 

(a) Effective Date 

This AD becomes effective December 17, 

2014. 

(b) Affected ADs 

(1) This AD replaces AD 2013–20–06, 

Amendment 39–17612 (78 FR 64156, October 

28, 2013). 

(2) This AD affects the requirements of the 

ADs specified in paragraphs (j)(1) through 

(j)(9) of this AD. 

(c) Applicability 

This AD applies to Airbus Model A340– 

211, –212, –213, –311, –312, –313, –541, and 

–642 airplanes, certificated in any category, 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a determination 

that existing maintenance requirements are 

not adequate to address the aging effects of 

aircraft systems. We are issuing this AD to 

address the aging effects of aircraft systems. 

Such aging effects could change the 

characteristics of systems life-limited 

components leading to an increased potential 

for failure, which, in isolation or in 

combination with one or more other specific 

failures or events, could result in failure of 

certain life limited parts, which could reduce 

the structural integrity or the controllability 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance/Inspection Program 

Revision 

Within 6 months after the effective date of 

this AD, revise the maintenance program or 

inspection program, as applicable, by 

incorporating Airbus A340 Airworthiness 

Limitations Section (ALS) Part 4—Ageing 

Systems Maintenance, Revision 03, dated 

November 15, 2012. The initial compliance 

times for the actions are within the 

applicable compliance time specified in the 

Record of Revisions page of Airbus A340 

ALS Part 4—Ageing Systems Maintenance, 

Revision 03, dated November 15, 2012, or 

within 6 months after the effective date of 

this AD, whichever is later, except as 

required by paragraph (h) of this AD. 

(h) Exceptions to Initial Compliance Times 

(1) Where Airbus A340 ALS Part 4— 

Ageing Systems Maintenance, Revision 03, 

dated November 15, 2012, defines a calendar 

compliance time for the modification of 

spoiler servo-controls having part numbers 

MZ4339390–01X; MZ4306000–01X; 

MZ4339390–02X; MZ4306000–02X; 

MZ4339390–10X; and MZ4306000–10X as 

‘‘March 5, 2010,’’ the calendar compliance 

time is April 14, 2011 (18 months after 

October 14, 2009 (the effective date of AD 

2009–18–20, Amendment 39–16017 (74 FR 

46313, September 9, 2009)). 

(2) Where Note 6 of ‘‘ATA 27–64, Flight 

Control—Spoiler Hydraulic Actuation, (Fig. 

09),’’ of Sub-part 4–2–1, Life Limits, of Subpart 4–2, Systems Life—Limited 

Components, of the Airbus A340 ALS, Part 

4—Ageing Systems Maintenance, Revision 

03, dated November 15, 2012, defines a 

calendar date of ‘‘September 5, 2008,’’ as a 

date for the determination of accumulated 

flight cycles since the aircraft’s initial entry 

into service, the calendar compliance time is 

October 14, 2009 (the effective date of AD 

2009–18–20, Amendment 39–16017 (74 FR 

46313, September 9, 2009)). 

(3) Where Note 6 of ‘‘ATA 27–64 Flight 

Control—Spoiler Hydraulic Actuation, (Fig. 

09),’’ of Sub-part 4–2–1, Life Limits, of Subpart 4–2, Systems Life—Limited 

Components, of the Airbus A340 ALS, Part 

4—Ageing Systems Maintenance, Revision 

03, dated November 15, 2012, defines a 

calendar compliance time of ‘‘March 5, 

2010,’’ for the modification of affected servocontrols, the calendar compliance time is 

April 14, 2011 (18 months after October 14, 

2009 (the effective date of AD 2009–18–20, 

Amendment 39–16017 (74 FR 46313, 

September 9, 2009)). 

(i) Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

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

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k)(1) of 

this AD. 

(j) Terminating Action for Other ADs 

Accomplishing the revision of the 

maintenance program and complying with all 

applicable instructions and airworthiness 

limitations required by paragraph (g) of this 

AD terminates the requirements of the ADs 

specified in paragraphs (j)(1) through (j)(9) of 

this AD for Model A340 airplanes only. 

(1) AD 2003–14–11, Amendment 39–13230 

(68 FR 41521, July 14, 2003). 

(2) AD 2004–11–08, Amendment 39–13654 

(69 FR 31874, June 8, 2004). 

(3) AD 2004–13–25, Amendment 39–13707 

(69 FR 41394, July 9, 2004). 

(4) AD 2004–18–14, Amendment 39–13793 

(69 FR 55326, September 14, 2004). 

(5) AD 2007–05–12, Amendment 39–14973 

(72 FR 10057, March 7, 2007). 

(6) AD 2008–06–07, Amendment 39–15419 

(73 FR 13103, March 12, 2008; corrected 

April 15, 2008 (73 FR 20367)). 

(7) AD 2009–18–20, Amendment 39–16017 

(74 FR 46313, September 9, 2009). 

(8) AD 2010–15–02, Amendment 39–16368 

(75 FR 42589, July 22, 2010). 

(9) AD 2012–04–07, Amendment 39–16963 

(77 FR 12989, March 5, 2012). 

(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: As of the 

effective date of this AD, 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. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0269, dated November 7, 

2013, for related information. You may 

examine the MCAI on the Internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2014–0776. 

(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 A340 Airworthiness Limitations 

Section (ALS) Part 4—Ageing Systems 

Maintenance, Revision 03, dated November 

15, 2012. The revision date of this document 

is not identified on the title page of this 

document. Also, the revision level of this 

document is identified on only the title page 

and in the Record of Revisions section of this 

document. 

(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 

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71308 Federal Register / Vol. 79, No. 231 / Tuesday, December 2, 2014 / Rules and Regulations 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on 

November 13, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27632 Filed 12–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0433; Directorate 

Identifier 94–ANE–39–AD; Amendment 39– 

18041; AD 2014–24–08] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 98–07–07 

for all Rolls-Royce plc (RR) RB211– 

535E4 and RB211–535E4–B turbofan 

engines. AD 98–07–07 required 

removing certain part number (P/N) 

low-pressure (LP) fuel filter-to-highpressure (HP) fuel pump tube 

assemblies and installing flexible LP 

fuel filter-to-HP fuel pump tube 

assemblies. This AD expands the 

applicability of AD 98–07–07 to include 

the RB211–535E4–C–37 turbofan engine 

and requires removal from service of 

additional P/N LP fuel filter-to-highpressure HP fuel pump tube assemblies. 

This AD was prompted by reports of 

fuel leaks that have resulted in a 

number of engine in-flight shutdowns. 

We are issuing this AD to prevent loss 

of fuel supply to the engine, which 

could lead to an in-flight shutdown of 

one or more engines, loss of thrust 

control, and damage to the airplane. 

DATES: This AD is effective January 6, 

2015. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, England, DE24 8BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936; email: http://

www.rolls-royce.com/contact/civil_

team.jsp; Internet: https://

www.aeromanager.com. You may view 

this service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, 

MA. For information on the availability 

of this material at the FAA, call 781– 

238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0433; 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 mandatory 

continuing airworthiness information, 

regulatory evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is Document 

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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Kenneth Steeves, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7765; fax: 781–238– 

7199; email: kenneth.steeves@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 98–07–07, 

Amendment 39–10426 (63 FR 18119, 

April 14, 1998), (‘‘AD 98–07–07’’). AD 

98–07–07 applied to the specified 

products. The NPRM published in the 

Federal Register on July 24, 2014 (79 FR 

42989). The NPRM proposed to expand 

the applicability of AD 98–07–07 to 

include the RB211–535E4–C–37 

turbofan engine and added two 

additional P/Ns identified for removal. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Support for the NPRM as Proposed 

United Airlines supports issuing the 

NPRM (79 FR 42989, July 24, 2014) as 

proposed. 

Request To Change the Compliance 

FedEx Express requested that the 

proposed AD require removal of only 

fuel tube assemblies, P/Ns 163521538 

and 163521545. These are the only fuel 

tube assemblies that are required to be 

removed by RR Service Bulletin No. 

RB.211–73–H131 and European 

Aviation Safety Agency AD 2014–0123. 

We do not agree. This AD will 

supersede AD 98–07–07. AD 98–07–07 

required the removal of fuel tube 

assemblies, P/Ns UL16692 and 

AE709623–1. Continuing to include 

these P/Ns would ensure, in the 

unlikely event that there is an engine 

containing fuel tube assemblies, P/Ns 

UL16692 and AE709623–1, that these 

fuel tube assemblies would still be 

removed. We did not change this AD. 

Change to the Compliance 

We changed paragraph (e)(2) of this 

AD to mandate installation of LP fuel 

filter-to-HP fuel pump tube assemblies 

eligible for installation. Paragraph (e)(2) 

was changed to support the Costs of 

Compliance as proposed in the NPRM 

(79 FR 42989, July 24, 2014). 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We 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 500 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 7.33 hours per engine to 

comply with this AD. The average labor 

rate is $85 per hour. Required parts cost 

about $10,000 per engine. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$5,311,525. 

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 

This AD will not have federalism 

implications under Executive Order 

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