Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 70447 

(h) Replacement of Forward Crew Oxygen 

Supply Hose 

For airplanes identified as Group 2 in 

Boeing Alert Service Bulletin B787–81205– 

SB350001–00, Issue 001, dated August 22, 

2013: Within 60 months after the effective 

date of this AD, replace the forward crew 

oxygen supply hose with a new nonconductive forward oxygen supply hose, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

B787–81205–SB350001–00, Issue 001, dated 

August 22, 2013. 

(i) Exception to Service Information 

Paragraph III.A., ‘‘Verification,’’ of B/E 

Aerospace Service Bulletin 4421086–35–001, 

Rev. 002, dated July 9, 2013, has a 

typographical error. The last sentence in that 

paragraph states, ‘‘If the decal shows PN 

4421086–101, continue with the retrofit steps 

in paragraph II.B.’’ The sentence should refer 

to paragraph III.B. of B/E Aerospace Service 

Bulletin 4421086–35–001, Rev. 002, dated 

July 9, 2013. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a distribution manifold 

having B/E Aerospace P/N 4421086–101; a 

flexible supply hose having B/E Aerospace P/ 

N 4421189–016; or a supply hose having 

Boeing P/N 4421189–023; on any airplane. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l) of this AD. Information may be 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

For more information about this AD, 

contact Susan Monroe, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, Seattle Aircraft 

Certification Office, FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 425– 

917–6457; fax: 425–917–6590; email: 

susan.l.monroe@faa.gov. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin B787– 

81205–SB350001–00, Issue 001, dated 

August 22, 2013. 

(ii) B/E Aerospace Service Bulletin 

4421086–35–001, Rev. 002, dated July 9, 

2013. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

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

5680; Internet https://

www.myboeingfleet.com. 

(4) For B/E service information identified 

in this AD, contact B/E Aerospace, Inc., 

Commercial Aircraft Products Group, 10800 

Pfluum Road, Lenexa, KS 66215; phone: 913– 

338–9800; fax: 913–469–8419. 

(5) You may view this service information 

at 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. 

(6) 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 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27359 Filed 11–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0132; Directorate 

Identifier 2012–NM–007–AD; Amendment 

39–18023; AD 2014–23–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2004–16– 

01 for certain Airbus Model A330–200 

and –300 series airplanes and Model 

A340–200 and –300 series airplanes. AD 

2004–16–01 required repetitive 

inspections for cracking of the chromed 

area of the left and right piston rods for 

the main landing gear (MLG) retraction 

actuators, and related investigative and 

corrective actions if necessary. This new 

AD requires repetitive draining of any 

fluid from the retraction actuator piston 

rod internal volume and sealing of the 

vent hole; repetitive ultrasonic 

inspections of the upper end of the 

piston rods, and corrective actions if 

necessary; a one-time ultrasonic 

inspection (longitudinal and 

circumferential) of the full length of the 

piston rod, and corrective actions if 

necessary; and a terminating 

modification of the left-hand and righthand MLG retraction actuators. This AD 

was prompted by reports of the piston 

rods for the MLG retraction actuators 

rupturing during flight. We are issuing 

this AD to prevent cracking of the piston 

rods for the MLG retraction actuators, 

which could result in rupture of a 

piston rod, non-damped extension of 

the MLG, high loads on the fully 

extended MLG, and consequent reduced 

structural integrity of the MLG. 

DATES: This AD becomes effective 

December 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 31, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 19, 2004 (69 FR 

46979, August 4, 2004). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2014-0132; 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, 

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70448 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

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 to supersede AD 2004–16–01, 

Amendment 39–13757 (69 FR 46979, 

August 4, 2004). AD 2004–16–01 

applied to certain Airbus Model A330– 

200 and –300 series airplanes and 

Model A340–200 and –300 series 

airplanes. The NPRM published in the 

Federal Register on February 6, 2014 

(79 FR 7098; corrected March 20, 2014 

(79 FR 15555)). The NPRM was 

prompted by reports of the piston rods 

for the MLG retraction actuators 

rupturing during flight. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2011– 

0178R1, dated March 6, 2012, corrected 

March 7, 2012 (for Model A340–200 and 

–300 series airplanes); and EASA AD 

2011–0179R1, dated March 6, 2012 (for 

Model A330–200 and –300 series 

airplanes) (both referred to after this as 

the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’); to correct an unsafe condition 

for the specified products. EASA AD 

2011–0178R1, dated March 6, 2012, 

corrected March 7, 2012, states: 

During an approach phase, the flight crew 

of an A330 aeroplane had to perform a freefall extension of the left-hand (LH) MLG. 

Rupture of the LH MLG retraction actuator 

piston rod was found near the rod attachment 

point. The inspection revealed at the location 

of the rupture the presence of corrosion 

resulting from incorrect application of the 

anticorrosion protection, and circumferential 

cracks resulting from normal operational 

loading effects. 

Since the above rupture, new cases of crack 

propagation along the length of the piston 

rod occurred. These ruptures led to a nondamped extension of the landing gear. Fully 

extended, the landing gear assembly was 

submitted to high loads jeopardising its 

structural integrity. 

This condition, if not detected and 

corrected, could lead to MLG failure during 

landing or roll-out and consequent damage to 

the aeroplane and injury to occupants. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued AD F–2005–098 [http:// 

ad.easa.europa.eu/blob/easa_ad_2005_5887_

F20050980tb_superseded.pdf/AD_F-2005- 

098_1] (EASA approval 2005–5887) [and AD 

F–2005–099 [http://ad.easa.europa.eu/blob/

easa_ad_2005_5888_F20050990tb_

superseded.pdf/AD_F-2005-099_2] (EASA 

approval 2005–5888)] to address this unsafe 

condition [the FAA issued AD 2004–16–01, 

Amendment 39–13757 (69 FR 46979, August 

4, 2004)]. Since that [DGAC France] AD was 

issued, the results of extensive investigation 

determined that the presence of water in the 

internal volume of the piston rod can lead to 

the formation of ice which represents a 

potential source of high magnitude tensile 

hoop stresses in the material of the rod, 

leading to propagation of longitudinal crack 

in the body of the piston rod. 

Prompted by these findings, EASA issued 

AD 2006–0301 [http://ad.easa.europa.eu/

blob/easa_ad_2006_0301_R2_

superseded.pdf/AD_2006-0301R2_1], 

partially retaining the requirements of DGAC 

France AD F–2005–099, which was 

superseded, and to revise the inspection 

requirements as follows: 

a. Extend the repetitive inspections 

interval for the removal of fluid from the 

internal volume of the piston rod using flight 

cycles in lieu of flight hours as this better 

represents the mechanism for the 

accumulation of water within the piston rod. 

b. Remove the preliminary visual 

inspection from the ultrasonic longitudinal 

inspection of the upper end of the piston rod. 

c. Add a new one-time ultrasonic 

longitudinal and circumferential inspection 

of the full piston rod length to eliminate any 

parts that exhibit severe corrosion along the 

internal length of the piston rod. 

d. Require installation of new design 

hollow piston rod Part Number (P/N) 

114256328 (Airbus mod. 52980—SB A340– 

32–4222 Revision 01) without a vent hole, 

thus eliminating moisture ingress as the 

terminating action. 

EASA AD 2006–0301 was later revised: 

—at revision 01, to correct a number of 

typographical errors and to add reference 

to Airbus SB A340–32–4212 Revision 04, 

and 

—at revision 02 to extend the inspections 

threshold from 3 to 6 years in service usage 

for retraction actuator piston rod P/N 

114256321 issue 06 which was reidentified to P/N 114256326 issue 01 in 

accordance with the instructions of Airbus 

SB A340–32–4260. 

More recently, the sampling of piston rod 

P/N 114256326 issue 1 and P/N 114256321 

issue 06 have confirmed the need to replace 

all retraction actuator piston rods with a 

piston rod P/N114256328. 

For the reasons described above, this 

[EASA] AD at original issue retained the 

requirements of EASA AD 2006–0301R2 

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

2006_0301_R2_superseded.pdf/AD_2006- 

0301R2_1), which is superseded, and 

required the replacement of all retraction 

actuator piston rods with a piston rod P/N 

114256328, which constitutes terminating 

action to the repetitive requirements of this 

AD. 

This [EASA] AD is revised to clarify that 

aeroplanes on which Airbus mod. 52980 has 

been embodied in production are not 

required to accomplish the reidentification of 

MLG retraction actuator P/N 114256002–055 

which is mentioned in the accomplishment 

instructions of Airbus SB A340–32–4222 

Revision 03. 

This [EASA] AD has been republished to 

correct a typographical mistake of the 

applicable Airbus SB number in the 

Applicability (in the Note) and in the Reason 

sections of this [EASA] AD. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0132- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 7098, 

February 6, 2014; corrected March 20, 

2014 (79 FR 15555)), and the FAA’s 

response to each comment. 

Request To Reference Latest Service 

Information 

Delta Airlines requested that we 

reference the latest Airbus service 

information, which is Airbus Service 

Bulletin A330–32–3180, Revision 05, 

dated January 27, 2014. Delta Airlines 

further requested that we provide credit 

for actions previously accomplished 

using Airbus Service Bulletin A330–32– 

3180, Revision 03, dated January 28, 

2011; and Airbus Service Bulletin 

A330–32–3180, Revision 04, dated July 

30, 2013. 

We agree with Delta Airlines’ 

comment to reference the latest service 

information. Airbus Service Bulletin 

A330–32–3180, Revision 05, dated 

January 27, 2014, provides the latest 

information on the modification 

required by this AD. This service 

bulletin specifies two additional workhours for re-identification of the part 

number of the MLG retraction actuator 

for Model A330–200 and –300 series 

airplanes at configuration 3, which were 

modified as described in Airbus Service 

Bulletin A330–32–3180, Revision 03, 

dated January 28, 2011. Reidentification of the MLG retraction 

actuator may be considered as a logical 

outgrowth of the proposed AD (79 FR 

7098, February 6, 2014; corrected March 

20, 2014 (79 FR 15555)) requirements. 

Airbus has also released Service 

Bulletin A340–32–4222, Revision 04, 

dated July 30, 2013. This service 

bulletin also specifies two additional 

work-hours for re-identification of the 

part number of the MLG retraction 

actuator for Model A340 series 

airplanes. There are currently no U.S.- 

registered Model A340 series airplanes. 

We have revised paragraphs (s) and (t) 

of this AD to specify Airbus Service 

Bulletin A330–32–3180, Revision 05, 

dated January 27, 2014; and Airbus 

Service Bulletin A340–32–4222, 

Revision 04, dated July 30, 2013; as the 

appropriate sources of service 

information for the required actions in 

those paragraphs. We have also revised 

paragraphs (w)(2) and (w)(3) of this AD 

to provide credit for previous actions 

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Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 70449 

accomplished using Airbus Service 

Bulletin A330–32–3180, Revision 03, 

dated January 28, 2011; Airbus Service 

Bulletin A330–32–3180, Revision 04, 

dated July 30, 2013; and Airbus Service 

Bulletin A340–32–4222, Revision 03, 

dated January 28, 2011; as applicable. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (79 FR 7098, February 

6, 2014; corrected March 20, 2014 (79 

FR 15555)), we proposed to prevent the 

use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (79 FR 7098, February 6, 2014; 

corrected March 20, 2014 (79 FR 15555)) 

about these proposed changes. However, 

a comment was provided for an NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013). The commenter stated the 

following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, the European Aviation 

Safety Agency (EASA), or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013) pointed out that in many cases the 

foreign manufacturer’s service bulletin 

and the foreign authority’s MCAI might 

have been issued some time before the 

FAA AD. Therefore, the DOA might 

have provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘DAH with State of 

Design Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH. 

Conclusion 

We reviewed the available data, 

including 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 changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 7098, 

February 6, 2014; corrected March 20, 

2014 (79 FR 15555)) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 7098, 

February 6, 2014; corrected March 20, 

2014 (79 FR 15555)). 

We also 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 24 

Model A330–200 and –300 series 

airplanes of U.S. registry. There are no 

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70450 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

Model A340–200 or –300 series 

airplanes of U.S. registry. 

We estimate that it will take about 67 

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 $56,000 

per product (2 actuators). Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$1,480,680, or $61,695 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 38 work-hours and require parts 

costing $56,000 (2 actuators), for a cost 

of $59,230 per product. We have no way 

of determining the number of aircraft 

that might need these actions. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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-2014-0132; 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 

removing Airworthiness Directive (AD) 

2004–16–01, Amendment 39–13757 (69 

FR 46979, August 4, 2004), and adding 

the following new AD: 

2014–23–07 Airbus: Amendment 39–18023. 

Docket No. FAA–2014–0132; Directorate 

Identifier 2012–NM–007–AD. 

(a) Effective Date 

This AD becomes effective December 31, 

2014. 

(b) Affected ADs 

This AD replaces AD 2004–16–01, 

Amendment 39–13757 (69 FR 46979, August 

4, 2004). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –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; all manufacturer serial 

numbers, except for those airplanes that have 

had Airbus Modification 52980 incorporated 

in production on both main landing gear 

(MLG) units, or airplanes that have had 

Airbus Modification 54500 incorporated in 

production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by reports of the 

piston rods for the MLG retraction actuators 

rupturing during flight. We are issuing this 

AD to prevent cracking of the piston rods for 

the MLG retraction actuators, which could 

result in rupture of a piston rod, non-damped 

extension of the MLG, high loads on the fully 

extended MLG, and consequent reduced 

structural integrity of the MLG. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Detailed Inspections 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do a 

detailed inspection for cracking of the visible 

chromed area of the MLG retraction actuator 

piston rods in the fully extended position, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3173, Revision 05, dated September 26, 

2008 (for Model A330–200 and –300 series 

airplanes); or Airbus Service Bulletin A340– 

32–4212, Revision 05, dated September 26, 

2008 (for Model A340–200 and –300 series 

airplanes). Repeat the inspection thereafter at 

intervals not to exceed 8 days until the 

actions required by paragraphs (j) and (o) of 

this AD are accomplished. 

(1) For MLG retraction actuator piston rods 

that have not had a detailed inspection 

accomplished as of the effective date of this 

AD, as described in any applicable service 

information specified in paragraph (h)(1) or 

(h)(2) of this AD: At the applicable time 

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specified in paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD. 

(i) For MLG retraction actuator piston rods 

having part number (P/N) 114256309 or P/N 

114256321 issue 03: Do the inspection within 

60 days after the effective date of this AD, or 

before the MLG retraction actuator has been 

in service 36 months, whichever occurs later. 

(ii) For MLG retraction actuator piston rods 

having P/N 114256326 issue 01 or P/N 

114256321 issue 06: Do the inspection within 

60 days after the effective date of this AD, or 

before the MLG retraction actuator has been 

in service 72 months, whichever occurs later. 

(2) For MLG retraction actuator piston rods 

having P/N 114256309, P/N 114256321 issue 

03, P/N 114256326 issue 01, or P/N 

114256321 issue 06, that have had a detailed 

inspection accomplished as of the effective 

date of this AD, as described in the 

applicable service information specified in 

paragraph (h)(1) or (h)(2) of this AD: Inspect 

within 8 days after the effective date of this 

AD. 

(h) Service Information for Determining 

Airplane Configuration for the Actions 

Required by Paragraph (g) of This AD 

(1) For Model A330–200 and –300 series 

airplanes: 

(i) Airbus Service Bulletin A330–32–3173, 

Revision 01, dated June 16, 2004; 

(ii) Airbus Service Bulletin A330–32–3173, 

Revision 02, dated May 11, 2005; 

(iii) Airbus Service Bulletin A330–32– 

3173, Revision 03, dated March 13, 2006; 

(iv) Airbus Service Bulletin A330–32– 

3173, Revision 04, dated June 12, 2006; or 

(v) Airbus Service Bulletin A330–32–3173, 

Revision 05, dated September 26, 2008. 

(2) For Model A340–200 and –300 series 

airplanes: 

(i) Airbus Service Bulletin A340–32–4212, 

Revision 01, dated June 16, 2004; 

(ii) Airbus Service Bulletin A340–32–4212, 

Revision 02, dated May 11, 2005; 

(iii) Airbus Service Bulletin A340–32– 

4212, Revision 03, dated March 13, 2006; 

(iv) Airbus Service Bulletin A340–32– 

4212, Revision 04, dated June 12, 2006; or 

(v) Airbus Service Bulletin A340–32–4212, 

Revision 05, dated September 26, 2008. 

(i) Corrective Action for Cracking 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD: Before further flight, replace the MLG 

retraction actuator with a new or serviceable 

part, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3173, Revision 05, 

dated September 26, 2008 (for Model A330– 

200 and –300 series airplanes); or Airbus 

Service Bulletin A340–32–4212, Revision 05, 

dated September 26, 2008 (for Model A340– 

200 and –300 series airplanes). 

(j) Repetitive Fluid Draining and Vent Hole 

Sealing 

At the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD: Drain any 

fluid from the retraction actuator piston rod 

internal volume and seal the vent hole, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3173, Revision 05, dated September 26, 

2008 (for Model A330–200 and –300 series 

airplanes); or Airbus Service Bulletin A340– 

32–4212, Revision 05, dated September 26, 

2008 (for Model A340–200 and –300 series 

airplanes). Repeat the draining and sealing 

thereafter at intervals not to exceed 1,000 

flight cycles or 24 months, whichever occurs 

first. 

(1) For MLG retraction actuator piston rods 

that have not been inspected and have not 

had the fluid drained as of the effective date 

of this AD, as described in the applicable 

service information specified in paragraph 

(k)(1) or (k)(2) of this AD: At the applicable 

time specified in paragraph (j)(1)(i) or 

(j)(1)(ii) of this AD. 

(i) For MLG retraction actuator piston rods 

having P/N 114256309 or P/N 114256321 

issue 03: Do the draining and sealing within 

60 days after the effective date of this AD, or 

before the MLG retraction actuator has been 

in service 36 months, whichever occurs later. 

(ii) For MLG retraction actuator piston rods 

having P/N 114256326 issue 01 or P/N 

114256321 issue 06: Do the draining and 

sealing within 60 days after the effective date 

of this AD, or before the MLG retraction 

actuator has been in service 72 months, 

whichever occurs later. 

(2) For MLG retraction actuator piston rods 

having P/N 114256309, P/N 114256321 issue 

03, P/N 114256326 issue 01, or P/N 

114256321 issue 06, that have been inspected 

and the fluid drained as of the effective date 

of this AD, as described in the applicable 

service information specified in paragraph 

(k)(1) or (k)(2) of this AD: Do the draining 

and sealing at the later of the times specified 

in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. 

(i) Within 1,000 flight cycles or 24 months, 

whichever occurs first, from the last 

inspection and fluid drainage accomplished 

in accordance with the requirements of 

paragraph (j) of this AD. 

(ii) Within 60 days after the effective date 

of this AD. 

(k) Service Information for Determining 

Airplane Configuration for the Actions 

Required by Paragraph (j) of This AD 

(1) For Model A330–200 and –300 series 

airplanes: 

(i) Airbus Service Bulletin A330–32–3173, 

Revision 02, dated May 11, 2005; 

(ii) Airbus Service Bulletin A330–32–3173, 

Revision 03, dated March 13, 2006; 

(iii) Airbus Service Bulletin A330–32– 

3173, Revision 04, dated June 12, 2006; or 

(iv) Airbus Service Bulletin A330–32– 

3173, Revision 05, dated September 26, 2008. 

(2) For Model A340–200 and –300 series 

airplanes: 

(i) Airbus Service Bulletin A340–32–4212, 

Revision 02, dated May 11, 2005; 

(ii) Airbus Service Bulletin A340–32–4212, 

Revision 03, dated March 13, 2006; 

(iii) Airbus Service Bulletin A340–32– 

4212, Revision 04, dated June 12, 2006; or 

(iv) Airbus Service Bulletin A340–32– 

4212, Revision 05, dated September 26, 2008. 

(l) Ultrasonic Inspection 

At the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD: Do an 

ultrasonic longitudinal inspection for 

cracking of the retraction actuator piston rod 

end, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3173, Revision 05, dated September 26, 

2008 (for Model A330–200 and –300 series 

airplanes); or Airbus Service Bulletin A340– 

32–4212, Revision 05, dated September 26, 

2008 (for Model A340–200 and –300 series 

airplanes). 

(1) For MLG retraction actuator piston rods 

that have not had a non-destructive test 

(NDT) inspection as of the effective date of 

this AD, as described in the applicable 

service information specified in paragraph 

(m)(1) or (m)(2) of this AD: At the applicable 

time specified in paragraph (l)(1)(i) or 

(l)(1)(ii) of this AD. 

(i) For MLG retraction actuator piston rods 

having P/N 114256309 or P/N 114256321 

issue 03: Do the inspection within 60 days 

after the effective date of this AD, or before 

the MLG retraction actuator has been in 

service 36 months, whichever occurs later. 

(ii) For MLG retraction actuator piston rods 

having P/N 114256326 issue 01 or P/N 

114256321 issue 06: Do the inspection within 

60 days after the effective date of this AD, or 

before the MLG retraction actuator has been 

in service 72 months, whichever occurs later. 

(2) For MLG retraction actuator piston rods 

having P/N 114256309, P/N 114256321 issue 

03, P/N 114256326 issue 01, or P/N 

114256321 issue 06, that have had an NDT 

inspection as of the effective date of this AD, 

as described in the applicable service 

information specified in paragraph (m)(1) or 

(m)(2) of this AD: Do the inspection at the 

later of the times specified in paragraphs 

(l)(2)(i) and (l)(2)(ii) of this AD. 

(i) Within 1,400 flight hours, 250 flight 

cycles, or 4 months, whichever occurs first 

after the date of the last ultrasonic 

longitudinal inspection performed as 

described in the applicable service 

information specified in paragraph (m)(1) or 

(m)(2) of this AD. 

(ii) Within 60 days after the effective date 

of this AD. 

(m) Service Information for Determining 

Airplane Configuration for the Actions 

Required by Paragraph (l) of This AD 

(1) For Model A330–200 and –300 series 

airplanes: 

(i) Airbus Service Bulletin A330–32–3173, 

dated December 17, 2003; 

(ii) Airbus Service Bulletin A330–32–3173, 

Revision 01, dated June 16, 2004; 

(iii) Airbus Service Bulletin A330–32– 

3173, Revision 02, dated May 11, 2005; 

(iv) Airbus Service Bulletin A330–32– 

3173, Revision 03, dated March 13, 2006; 

(v) Airbus Service Bulletin A330–32–3173, 

Revision 04, dated June 12, 2006; or 

(vi) Airbus Service Bulletin A330–32– 

3173, Revision 05, dated September 26, 2008. 

(2) For Model A340–200 and –300 series 

airplanes: 

(i) Airbus Service Bulletin A340–32–4212, 

dated December 17, 2003; 

(ii) Airbus Service Bulletin A340–32–4212, 

Revision 01, dated June 16, 2004; 

(iii) Airbus Service Bulletin A340–32– 

4212, Revision 02, dated May 11, 2005; 

(iv) Airbus Service Bulletin A340–32– 

4212, Revision 03, dated March 13, 2006; 

(v) Airbus Service Bulletin A340–32–4212, 

Revision 04, dated June 12, 2006; or 

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(vi) Airbus Service Bulletin A340–32– 

4212, Revision 05, dated September 26, 2008. 

(n) Corrective Action for Ultrasonic 

Inspection; Repetitive Interval 

(1) If the finding of the inspection required 

by paragraph (l) of this AD gives an 

indication of 75 percent or higher of full 

screen height (FSH) and between 5 and 7 in 

time base: Before further flight, replace the 

MLG retraction actuator with a new or 

serviceable part, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3173, Revision 05, 

dated September 26, 2008 (for Model A330– 

200 and –300 series airplanes); or Airbus 

Service Bulletin A340–32–4212, Revision 05, 

dated September 26, 2008 (for Model A340– 

200 and –300 series airplanes). 

(2) If the finding of the inspection required 

by paragraph (l) of this AD gives an 

indication of less than 75 percent FSH and 

between 5 and 7 in time base: Repeat the 

inspection required by paragraph (l) of this 

AD thereafter at intervals not to exceed 1,400 

flight hours, 250 flight cycles, or 4 months, 

whichever occurs first. 

(o) One-Time Ultrasonic Inspections of the 

Full-Length of the Piston Rod 

At the applicable time specified in 

paragraph (o)(1) or (o)(2) of this AD: Do a 

full-length ultrasonic longitudinal and a fulllength circumferential inspection of the 

chromium-plated area of the piston rod for 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3173, Revision 05, 

dated September 26, 2008 (for Model A330– 

200 and –300 series airplanes); or Airbus 

Service Bulletin A340–32–4212, Revision 05, 

dated September 26, 2008 (for Model A340– 

200 and –300 series airplanes). 

(1) For MLG retraction actuator piston rods 

having P/N 114256309 or P/N 114256321 

issue 03: Inspect at the later of the times 

specified in paragraphs (o)(1)(i) and (o)(1)(ii) 

of this AD. 

(i) Within 1,750 flight hours, 315 flight 

cycles, or 5 months after the effective date of 

this AD, whichever occurs first. 

(ii) Before the MLG retraction actuator has 

been in service 36 months. 

(2) For MLG retraction actuator piston rods 

having P/N 114256326 issue 01 or P/N 

114256321 issue 06: Inspect at the later of the 

times specified in paragraphs (o)(2)(i) and 

(o)(2)(ii) of this AD. 

(i) Within 1,750 flight hours, 315 flight 

cycles, or 5 months after the effective date of 

this AD, whichever occurs first. 

(ii) Before the MLG retraction actuator has 

been in service 72 months. 

(p) Corrective Action for One-Time 

Ultrasonic Inspections of the Full-Length of 

the Piston Rod 

(1) If the finding of the full-length 

ultrasonic longitudinal inspection required 

by paragraph (o) of this AD gives an 

indication of 75 percent or higher FSH and 

between 5 and 7 in time base: Before further 

flight, replace the MLG retraction actuator 

with a new or serviceable part, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–32–3173, 

Revision 05, dated September 26, 2008 (for 

Model A330–200 and –300 series airplanes); 

or Airbus Service Bulletin A340–32–4212, 

Revision 05, dated September 26, 2008 (for 

Model A340–200 and –300 series airplanes). 

(2) If the finding of the full-length 

ultrasonic circumferential inspection 

required by paragraph (o) of this AD gives an 

indication of 75 percent or higher FSH and 

between 7 and 9.5 in time base: Before 

further flight, replace the MLG retraction 

actuator with a new or serviceable part, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3173, Revision 05, dated September 26, 

2008 (for Model A330–200 and –300 series 

airplanes); or Airbus Service Bulletin A340– 

32–4212, Revision 05, dated September 26, 

2008 (for Model A340–200 and –300 series 

airplanes). 

(q) Reporting Requirement 

Report the results (regardless of findings) 

of the detailed inspection, the fluid drain/

seal of the retraction actuator piston rod, the 

one-time ultrasonic longitudinal inspection 

of the piston rod end, and the one-time fulllength ultrasonic longitudinal and 

circumferential inspection required by this 

AD, and the findings of the actions required 

by this AD that cause an actuator to be 

replaced, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3173, Revision 05, 

dated September 26, 2008 (for Model A330– 

200 and –300 series airplanes); or Airbus 

Service Bulletin A340–32–4212, Revision 05, 

dated September 26, 2008 (for Model A340– 

200 and –300 series airplanes). Submit the 

report to Airbus Customer Services 

Directorate, Attention: SEDCC1 Technical 

Data and Documentation Services fax: (+33) 

5 61 93 28 06; email: sb.reporting@

airbus.com; or via your Airbus resident 

customer support office. Submit the report at 

the applicable time specified in paragraph 

(q)(1) or (q)(2) of this AD. 

(1) If the actions requiring reporting, as 

specified in paragraph (q) of this AD, are 

done on or after the effective date of this AD: 

Submit the report within 90 days after those 

actions have been done. 

(2) If the actions requiring reporting, as 

specified in paragraph (q) of this AD, were 

done before the effective date of this AD: 

Submit the report within 90 days after the 

effective date of this AD. 

(r) Terminating Actions for Repetitive 

Detailed Inspections 

Accomplishment of the initial drainage of 

the fluid from the piston, as required by 

paragraph (j) of this AD; and the full-length 

ultrasonic longitudinal inspection, and the 

full-length circumferential inspection, as 

required by paragraph (o) of this AD; 

constitutes terminating action for the 

repetitive detailed inspections required by 

paragraph (g) of this AD, provided no crack 

is found during the inspections. 

(s) Terminating Modification 

Within 48 months after the effective date 

of this AD: Modify the left-hand and righthand MLG retraction actuators, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–32–3180, 

Revision 05, dated January 27, 2014 (for 

Model A330–200 and –300 series airplanes); 

or Airbus Service Bulletin A340–32–4222, 

Revision 04, dated July 30, 2013 (for Model 

A340–200 and –300 series airplanes). 

Accomplishment of the modification 

required by this paragraph terminates the 

repetitive requirements of this AD for the 

MLG retraction actuator that is modified. 

(t) Exception to Re-Identification of the MLG 

Retraction Actuator 

The re-identification of the MLG retraction 

actuator having P/N 114256002–055, which 

is described in Airbus Service Bulletin 

A330–32–3180, Revision 05, dated January 

27, 2014 (for Model A330–200 and –300 

series airplanes); and Airbus Service Bulletin 

A340–32–4222, Revision 04, dated July 30, 

2013 (for Model A340–200 and –300 series 

airplanes); is not required on airplanes that 

have Airbus modification 52980 embodied in 

production. 

(u) Optional Parts Installation 

Installation of a retraction actuator piston 

rod having P/N 114256323, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–32–3174, 

Revision 02, dated September 16, 2005 (for 

Model A330–200 and –300 series airplanes); 

or Airbus Service Bulletin A340–32–4213, 

Revision 01, dated September 16, 2005 (for 

Model A340–200 and –300 series airplanes); 

is an acceptable method of compliance with 

the requirements of paragraphs (g), (j), (l), 

and (o) of this AD for that installed MLG 

retraction actuator. 

(v) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a piston rod having P/N 

114256309, P/N 114256321, or P/N 

114256326 issue 01 for the MLG retraction 

actuator on any airplane, unless the part 

meets the applicable requirements of this AD 

at the specified times and intervals. 

(w) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraphs (g), (j), (l), and 

(o) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraphs (w)(1)(i) through (w)(1)(ix) of this 

AD. 

(i) Airbus Service Bulletin A330–32–3173, 

dated December 17, 2003; (for Model A330– 

200 and –300 series airplanes). 

(ii) Airbus Service Bulletin A330–32–3173, 

Revision 01, dated June 16, 2004 (for Model 

A330–200 and –300 series airplanes). 

(iii) Airbus Service Bulletin A330–32– 

3173, Revision 02, dated May 11, 2005 (for 

Model A330–200 and –300 series airplanes). 

(iv) Airbus Service Bulletin A330–32– 

3173, Revision 03, dated March 13, 2006 (for 

Model A330–200 and –300 series airplanes). 

(v) Airbus Service Bulletin A330–32–3173, 

Revision 04, dated June 12, 2006 (for Model 

A330–200 and –300 series airplanes). 

(vi) Airbus Service Bulletin A340–32– 

4212, dated December 17, 2003 (for Model 

A340–200 and –300 series airplanes). 

(vii) Airbus Service Bulletin A340–32– 

4212, Revision 01, dated June 16, 2004 (for 

Model A340–200 and –300 series airplanes). 

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(viii) Airbus Service Bulletin A340–32– 

4212, Revision 02, dated May 11, 2005; 

Revision 03, dated March 13, 2006 (for Model 

A340–200 and –300 series airplanes). 

(ix) Airbus Service Bulletin A340–32– 

4212, Revision 04, dated June 12, 2006 (for 

Model A340–200 and –300 series airplanes). 

(2) This paragraph provides credit for the 

actions required by paragraph (s) of this AD, 

if the modification was done before the 

effective date of this AD using the service 

information specified in paragraphs (u)(2)(i) 

through (u)(2)(iv) of this AD. These service 

bulletins are not incorporated by reference in 

this AD. 

(i) Airbus Service Bulletin A330–32–3180, 

Revision 01, dated August 15, 2005 for Model 

A330–200 and –300 series airplanes). 

(ii) Airbus Service Bulletin A330–32–3180, 

Revision 02, dated April 4, 2007 (for Model 

A330–200 and –300 series airplanes). 

(iii) Airbus Service Bulletin A330–32– 

3180, Revision 03, dated January 28, 2011. 

(iv) Airbus Service Bulletin A330–32– 

3180, Revision 04, dated July 30, 2013. 

(v) Airbus Service Bulletin A340–32–4222, 

Revision 01, dated August 15, 2005 (for 

Model A340–200 and –300 series airplanes). 

(vi) Airbus Service Bulletin A340–32– 

4222, Revision 02, dated April 4, 2007 (for 

Model A340–200 and –300 series airplanes). 

(vii) Airbus Service Bulletin A340–32– 

4222, Revision 03, dated January 28, 2011 

(for Model A340–200 and –300 series 

airplanes). 

(3) This paragraph provides credit for the 

actions required by paragraph (s) of this AD, 

if the modification was done before the 

effective date of this AD using Airbus Service 

Bulletin A340–32–4222, dated September 20, 

2004; and the re-identification was done 

before the effective date of this AD using 

Airbus Service Bulletin A340–32–4222, 

Revision 01, dated August 15, 2005, or 

Airbus Service Bulletin A340–32–4222, 

Revision 02, dated April 4, 2007. These 

service bulletins are not incorporated by 

reference in this AD. 

(x) 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(y) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2011–0178R1, dated March 6, 2012 

(corrected March 7, 2012); and Airworthiness 

Directive 2011–0179R1, dated March 6, 2012; 

for related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0132-0003. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (z)(5) and (z)(6) of this AD. 

(z) 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. 

(3) The following service information was 

approved for IBR on December 31, 2014. 

(i) Airbus Service Bulletin A330–32–3173, 

dated December 17, 2003. 

(ii) Airbus Service Bulletin A330–32–3173, 

Revision 02, dated May 11, 2005. 

(iii) Airbus Service Bulletin A330–32– 

3173, Revision 03, dated March 13, 2006. 

(iv) Airbus Service Bulletin A330–32– 

3173, Revision 04, dated June 12, 2006. 

(v) Airbus Service Bulletin A330–32–3173, 

Revision 05, dated September 26, 2008. 

(vi) Airbus Service Bulletin A330–32– 

3174, Revision 02, dated September 16, 2005. 

(vii) Airbus Service Bulletin A330–32– 

3180, Revision 05, dated January 27, 2014. 

(viii) Airbus Service Bulletin A340–32– 

4212, dated December 17, 2003. 

(ix) Airbus Service Bulletin A340–32– 

4212, Revision 02, dated May 11, 2005. 

(x) Airbus Service Bulletin A340–32–4212, 

Revision 03, dated March 13, 2006. 

(xi) Airbus Service Bulletin A340–32– 

4212, Revision 04, dated June 12, 2006. 

(xii) Airbus Service Bulletin A340–32– 

4212, Revision 05, dated September 26, 2008. 

(xiii) Airbus Service Bulletin A340–32– 

4213, Revision 01, dated September 16, 2005. 

(xiv) Airbus Service Bulletin A340–32– 

4222, Revision 04, dated July 30, 2013. 

(4) The following service information was 

approved for IBR on August 19, 2004 (69 FR 

46979, August 4, 2004). 

(i) Airbus Service Bulletin A330–32–3173, 

Revision 01, dated June 16, 2004. 

(ii) Airbus Service Bulletin A340–32–4212, 

Revision 01, dated June 16, 2004. 

(5) 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. 

(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 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26986 Filed 11–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0062; Directorate 

Identifier 2012–NM–031–AD; Amendment 

39–18025; AD 2014–23–09] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2000–17– 

03 for all Fokker Services B.V. Model 

F.28 Mark 0100 airplanes. AD 2000–17– 

mstockstill on DSK4VPTVN1PROD with RULES