Federal Register / Vol. 80, No. 154 / Tuesday, August 11, 2015 / Rules and Regulations 48019 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc (RR) 

RB211–524B–02, RB211–524B2–19, RB211– 

524B3–02, RB211–524B4–02, RB211–524B4– 

D–02, RB211–524C2–19, RB211–524D4–19, 

RB211–524D4–39, and RB211–524D4X–19 

turbofan engines with high-pressure turbine 

(HPT) blades, part numbers (P/Ns) UL32958 

and UL21691, installed. 

(d) Reason 

This AD was prompted by several failures 

of affected HPT blades. We are issuing this 

AD to prevent failure of the HPT blade, 

which could lead to failure of one or more 

engines, loss of thrust control, and damage to 

the airplane. 

(e) Actions and Compliance 

(1) Comply with this AD within the 

compliance times specified, unless already 

done. 

(2) After the effective date of this AD, 

within 2 months or before exceeding 6,500 

flight hours since first installation of HPT 

blades, P/Ns UL32958 and UL21691, on an 

engine, whichever occurs later, remove all 

affected HPT blades from service. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE–AD–AMOC@faa.gov. 

(g) Related Information 

(1) For more information about this AD, 

contact Katheryn Malatek, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7747; fax: 781–238– 

7199; email: katheryn.malatek@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0250, dated 

November 19, 2014, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2015–0095. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

July 30, 2015. 

Ann C. Mollica, 

Acting Assistant Directorate Manager, Engine 

& Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–19321 Filed 8–10–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0834; Directorate 

Identifier 2012–NM–045–AD; Amendment 

39–18227; AD 2015–16–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directives (AD) 2003–14– 

11, AD 2004–11–08, AD 2004–13–25, 

AD 2004–18–14, AD 2007–05–12, AD 

2008–06–07, AD 2009–18–20, AD 2010– 

15–02, and AD 2012–04–07 that apply 

to certain Airbus Model A330 and A340 

series airplanes. AD 2003–14–11, AD 

2004–11–08, AD 2004–13–25, AD 2004– 

18–14, AD 2007–05–12, AD 2008–06– 

07, AD 2009–18–20, AD 2010–15–02, 

and AD 2012–04–07 required revising 

the maintenance program to incorporate 

certain maintenance requirements and 

airworthiness limitations; replacing 

certain flap rotary actuators; repetitively 

inspecting elevator servo-controllers 

and pressure relief valves of the spoiler 

servo controls; repetitively testing the 

elevator servo control loops, modifying 

the elevator servo controls, and 

repetitively replacing certain retraction 

brackets of the main landing gear; and 

revising the airplane flight manual. This 

new AD requires revising the 

maintenance program or inspection 

program to incorporate certain 

maintenance requirements and 

airworthiness limitations. This new AD 

also removes Airbus Model A340–200, 

–300, –500, and –600 series airplanes 

from the applicability and adds Airbus 

Model A330–323 airplanes to the 

applicability. This AD was prompted by 

a determination that more restrictive 

maintenance requirements and 

airworthiness limitations are necessary. 

We are issuing this AD to address the 

aging effects of aircraft systems. Such 

aging effects could change the 

characteristics of those systems, 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 of the airplane or 

reduce the controllability of the 

airplane. 

DATES: This AD becomes effective 

September 15, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 15, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0834; 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0834. 

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 supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to revise the 

following airworthiness directives that 

applied to certain Airbus Model A330 

and A340 series 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 2009–18–20, Amendment 39– 

16017 (74 FR 46313, September 9, 

2009). 

• AD 2010–15–02, Amendment 39– 

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

• AD 2012–04–07, Amendment 39– 

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


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48020 Federal Register / Vol. 80, No. 154 / Tuesday, August 11, 2015 / Rules and Regulations 

The SNPRM published in the Federal 

Register on March 9, 2015 (80 FR 

12360). We preceded the SNPRM with 

a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on November 7, 2013 (78 FR 

66861). The NPRM was prompted by a 

determination that more restrictive 

maintenance requirements and 

airworthiness limitations were 

necessary. The NPRM proposed to 

supersede 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 2008–06–07, 

Amendment 39–15419 (73 FR 13103, 

March 12, 2008; corrected April 15, 

2008 (73 FR 20367)); and AD 2012–04– 

07, Amendment 39–16963 (77 FR 

12989, March 5, 2012) to require actions 

intended to address the aging effects of 

aircraft systems. The NPRM proposed to 

require revising the maintenance 

program or inspection program, as 

applicable, to incorporate certain 

maintenance requirements and 

airworthiness limitations. 

The SNPRM (80 FR 12360, March 9, 

2015) proposed to supersede AD 2007– 

05–12, Amendment 39–14973 (72 FR 

10057, March 7, 2007); AD 2009–18–20, 

Amendment 39–16017 (74 FR 46313, 

September 9, 2009); and AD 2010–15– 

02, Amendment 39–16368 (75 FR 

42589, July 22, 2010); in addition to 

those ADs already identified in the 

NPRM (78 FR 66861, November 7, 

2013), as well as to require more 

restrictive limitations and to add Airbus 

Model A330–323 airplanes to the 

applicability. We are issuing this AD to 

address the aging effects of aircraft 

systems. Such aging effects could 

change the characteristics of those 

systems, 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 of the airplane or reduce the 

controllability of the airplane. 

The European Aviation Safety Agency 

(EASA) which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0268, dated November 7, 

2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain Airbus 

Model A330 series airplanes. EASA AD 

2013–0268 supersedes and retains the 

requirements of four EASA ADs and 

requires accomplishment of the actions 

specified in Airbus A330 Airworthiness 

Limitations Section (ALS) Part 4—Aging 

Systems Maintenance, Revision 04, 

dated August 27, 2013. 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 A330 ALS Part 4, which is 

approved by EASA. 

Revision 04 of Airbus A330 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 2012–0020 [http://ad.easa.europa.eu/ad/ 

2012-0020], which is superseded, and 

requires accomplishment of the actions 

specified in Airbus A330 ALS Part 4 at 

Revision 04. 

In addition, this [EASA] AD also 

supersedes EASA AD 2006–0159 [http://

ad.easa.europa.eu/ad/2006-0159], EASA AD 

2008–0026 [http://ad.easa.europa.eu/ad/

2008-0026] and EASA AD 2008–0160 [http:// 

ad.easa.europa.eu/ad/2008-0160] [which 

correspond to FAA ADs 2007–05–12, 

Amendment 39–14973 (72 FR 10057, March 

7, 2007); 2010–15–02, Amendment 39–16368 

(75 FR 42589, July 22, 2010); and 2009–18– 

20, Amendment 39–16017 (74 FR 46313, 

September 9, 2009), respectively], whose 

requirements applicable to A330 aeroplanes 

have been transferred into Airbus A330 ALS 

Part 4. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2013–0834. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. An 

anonymous commenter supported the 

SNPRM (80 FR 12360, March 9, 2015). 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (80 FR 

12360, March 9, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (80 FR 12360, 

March 9, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus issued A330 Airworthiness 

Limitations Section (ALS) Part 4—Aging 

Systems Maintenance, Revision 04, 

dated August 27, 2013, and Airbus A330 

ALS Part 4—Aging Systems 

Maintenance (ASM), Variation 4.1 and 

Variation 4.2, both dated July 23, 2014. 

This service information describes 

preventative maintenance requirements 

and associated airworthiness limitations 

applicable to aircraft systems 

susceptible to aging effects. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this AD. 

Costs of Compliance 

We estimate that this AD affects 79 

airplanes of U.S. registry. 

We estimate that it will take about 2 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost $0 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $13,430, or $170 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. 


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Federal Register / Vol. 80, No. 154 / Tuesday, August 11, 2015 / Rules and Regulations 48021 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0834; 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 

■ a. Removing Airworthiness Directive 

(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 2009–18–20, 

Amendment 39–16017 (74 FR 46313, 

September 9, 2009); AD 2010–15–02, 

Amendment 39–16368 (75 FR 42589, 

July 22, 2010); AD 2012–04–07, 

Amendment 39–16963 (77 FR 12989, 

March 5, 2012); and 

■ b. Adding the following new AD: 

2015–16–02 Airbus: Amendment 39–18227. 

Docket No. FAA–2013–0834; Directorate 

Identifier 2012–NM–045–AD. 

(a) Effective Date 

This AD becomes effective September 15, 

2015. 

(b) Affected ADs 

This AD replaces the ADs specified in 

paragraphs (b)(1) through (b)(9) of this AD. 

(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). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –223F, –243F, 

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

–342, and –343 airplanes; certificated in any 

category; all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Unsafe Condition 

This AD was prompted by a determination 

that more restrictive maintenance 

requirements and airworthiness limitations 

are necessary. We are issuing this AD to 

address the aging effects of aircraft systems. 

Such aging effects could change the 

characteristics of those systems, 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 of the 

airplane or reduce the controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance Program Revision and 

Actions 

Within 6 months after the effective date of 

this AD, revise the maintenance program or 

inspection program, as applicable, by 

incorporating Airbus A330 Airworthiness 

Limitations Section (ALS) Part 4—Aging 

Systems Maintenance, Revision 04, dated 

August 27, 2013, and Airbus A330 ALS Part 

4—Aging Systems Maintenance (ASM), 

Variation 4.1 and Variation 4.2, both dated 

July 23, 2014. The initial compliance times 

for the actions are within the applicable 

compliance times specified in the Record of 

Revisions pages of Airbus A330 ALS Part 4— 

Aging Systems Maintenance, Revision 04, 

dated August 27, 2013, Airbus A330 ALS 

Part 4—Aging Systems Maintenance (ASM), 

Variation 4.1 and Variation 4.2, both dated 

July 23, 2014, 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 A330 ALS Part 4—Aging 

Systems Maintenance, Revision 04, dated 

August 27, 2013, defines a calendar 

compliance time for elevator servo-controls 

having part number (P/N) SC4800–2, 

SC4800–3, SC4800–4, SC4800–6, SC4800–7, 

or SC4800–8 as ‘‘August 31, 2004,’’ the 

calendar compliance time is June 13, 2007 

(34 months after August 13, 2004 (the 

effective date of AD 2004–13–25, 

Amendment 39–13707 (69 FR 41394, July 9, 

2004))). 

(2) Where Airbus A330 ALS Part 4—Aging 

Systems Maintenance, Revision 04, dated 

August 27, 2013, defines a calendar 

compliance time for spoiler servo-controls 

(SSCs) having P/N 1386A0000–01, P/N 

1386B0000–01, P/N 1387A0000–01 or P/N 

1387B0000–01 as ‘‘December 31, 2003,’’ the 

calendar compliance time is November 19, 

2005 (13 months after October 19, 2004 (the 

effective date of AD 2004–18–14, 

Amendment 39–13793 (69 FR 55326, 

September 14, 2004))). 

(3) Where Airbus A330 ALS Part 4—Aging 

Systems Maintenance, Revision 04, dated 

August 27, 2013, defines a calendar 

compliance time for elevator servo-controls 

having P/N SC4800–73, SC4800–93, SC4800– 

103 and SC4800–113 as ‘‘June 30, 2008,’’ the 

calendar compliance time is September 16, 

2009 (17 months after April 16, 2008 (the 

effective date of AD 2008–06–07, 

Amendment 39–15419 (73 FR 13103, March 

12, 2008; corrected April 15, 2008 (73 FR 

20367)))). 

(4) The initial compliance time for 

replacement of the retraction brackets of the 

main landing gear (MLG) having a part 

number specified in paragraphs (h)(4)(i) 

through (h)(4)(xvi) of this AD is before the 

accumulation of 19,800 total landings on the 

affected retraction brackets of the MLG, or 

within 900 flight hours after April 9, 2012 

(the effective date of AD 2012–04–07, 

Amendment 39–16963 (77 FR 12989, March 

5, 2012), whichever occurs later. 

(i) 201478303 

(ii) 201478304 

(iii) 201478305 

(iv) 201478306 

(v) 201478307 

(vi) 201478308 

(vii) 201428380 

(viii) 201428381 

(ix) 201428382 

(x) 201428383 

(xi) 201428384 

(xii) 201428385 

(xiii) 201428378 

(xiv) 201428379 


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(xv) 201428351 

(xvi) 201428352 

(5) Where Airbus A330 ALS Part 4—Aging 

Systems Maintenance, Revision 04, dated 

August 27, 2013, defines a calendar 

compliance time for the modification of SSCs 

on three hydraulic circuits having part 

numbers MZ4339390–01X, MZ4306000–01X, 

MZ4339390–02X, MZ4306000–02X, 

MZ4339390–10X, or 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))). 

(6) Where Note (6) of ‘‘ATA 27–64–00 

Flight Control—Spoiler Hydraulic 

Actuation,’’ of Sub-part 4–2–1, ‘‘Life Limits,’’ 

of Sub-part 4–2, ‘‘Systems Life Limited 

Components,’’ of Airbus A330 ALS Part 4— 

Aging Systems Maintenance, Revision 04, 

dated August 27, 2013, defines a calendar 

date of ‘‘September 5, 2008,’’ as a date for the 

determination of accumulated flight cycles 

since the aircraft initial entry into service, the 

date is October 14, 2009 (the effective date 

of AD 2009–18–20, Amendment 39–16017 

(74 FR 46313, September 9, 2009)). 

(7) Where Note (6) of ‘‘ATA 27–64–00 

Flight Control—Spoiler Hydraulic 

Actuation,’’ of Sub-part 4–2–1, ‘‘Life Limits,’’ 

of Sub-part 4–2, ‘‘Systems Life Limited 

Components,’’ of Airbus A330 ALS Part 4— 

Aging Systems Maintenance, Revision 04, 

dated August 27, 2013, defines a calendar 

compliance time as ‘‘March 5, 2010,’’ for the 

modification of affected servo controls, 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) No 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 (j)(1) of 

this AD. 

(j) 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- 

ACO-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. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) AD 2013– 

0268, dated November 7, 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–2013–0834. 

(l) 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 A330 Airworthiness Limitations 

Section ALS Part 4—Aging Systems 

Maintenance, Revision 04, dated August 27, 

2013. 

(ii) Airbus A330 ALS Part 4—Aging 

Systems Maintenance (ASM), Variation 4.1, 

dated July 23, 2014. 

(iii) Airbus A330 ALS Part 4—Aging 

Systems Maintenance (ASM), Variation 4.2, 

dated July 23, 2014. 

(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 July 28, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–19182 Filed 8–10–15; 08:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0751; Directorate 

Identifier 2013–NM–188–AD; Amendment 

39–18229; AD 2015–16–04] 

RIN 2120–AA64 

Airworthiness Directives; Kidde 

Graviner 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Kidde Graviner hand-operated fire 

extinguishers. This AD was prompted 

by a report that a fire extinguisher failed 

to operate when the activation lever was 

pressed. This AD requires modifying the 

affected fire extinguishers. We are 

issuing this AD to prevent fire 

extinguishers from failing to operate in 

the event of a fire, which could 

jeopardize occupants’ safety and 

continuation of safe flight and landing. 

DATES: This AD becomes effective 

September 15, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 15, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0751 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 Kidde Graviner 

Limited, Mathisen Way, Colnbrook, 

Slough, Berkshire, SL3 0HB, United 

Kingdom; telephone +44 (0) 1753 

583245; fax +44 (0) 1753 685040. 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0751. 

FOR FURTHER INFORMATION CONTACT: Ian 

Lucas, Aerospace Engineer, Boston 

Aircraft Certification Office (ACO), 

ANE–150, FAA, Engine and Propeller 

Directorate, 12 New England Executive 


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