Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 70453 

(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– 

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70454 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

03 required inspections of the nose 

landing gear (NLG) main fitting to detect 

cracking of the NLG main fitting 

subassembly, and corrective actions if 

necessary. This new AD retains the 

requirements of AD 2000–17–03, 

requires installing a new part number 

NLG unit that terminates the repetitive 

inspections, and adds airplanes to the 

applicability. This AD was prompted by 

a report of an NLG main fitting failure. 

We are issuing this AD to prevent 

cracking of the NLG main fitting, which 

could lead to collapse of the NLG during 

takeoff and landing, and possible injury 

to the flight crew and passengers. 

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 a certain other publication listed in 

this AD as of October 3, 2000 (65 FR 

52298, August 29, 2000). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0062; 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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 

1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.com. You may 

view this referenced service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2000–17–03, 

Amendment 39–11876 (65 FR 52298, 

August 29, 2000). AD 2000–17–03 

applied to all Fokker Services B.V. 

Model F.28 Mark 0100 airplanes. The 

NPRM published in the Federal 

Register on February 28, 2014 (79 FR 

11351). The NPRM proposed to 

continue to require a one-time visual 

inspection, and repetitive eddy current 

and dye penetrant inspections of the 

NLG main fitting to detect cracking of 

the NLG main fitting subassembly, and 

corrective actions if necessary. The 

NPRM also proposed to require 

installing a new part number NLG unit 

that would terminate the repetitive 

inspections, and adding airplanes to the 

applicability. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0002R1, 

dated March 30, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on all Fokker Services B.V. Model F.28 

Mark 0100 airplanes. The MCAI states: 

In 1997, a report was received concerning 

a Fokker 100 (F28 Mark 0100) aeroplane, 

where during landing following nose wheel 

touch-down, the nose landing gear (NLG) 

broke off just below the pintle pins. 

Subsequent inspection by the affected 

operator of other aeroplanes in the fleet 

identified three more suspect NLG main 

fittings. Eddy current (EC) and/or dye 

penetrant inspections of these units later 

confirmed that cracks were present on the 

inner side of the downlock plunger support 

web. The total number of flight cycles (FC) 

accumulated by the cracked NLG main 

fittings at the time of detection were between 

9,300 FC and 17,600 FC. 

This condition, if not detected and 

corrected, could result in further incidents of 

NLG collapse, possibly resulting in damage 

to the aeroplane and/or injury to the 

occupants. To address this potential unsafe 

condition [Civil Aviation Authority 

—Netherlands] CAA–NL issued [an] AD 

* * * to require repetitive inspections of the 

NLG main fitting and, depending on findings, 

rework or replacement of the NLG main 

fitting. 

Since [that Netherlands] AD * * * was 

issued, it was determined that replacement of 

a Messier-Dowty (M–D, formerly Dowty 

Rotol) Part Number (P/N) 201071001 or P/N 

201071002 NLG with, respectively, a P/N 

201071003 or P/N 201071004 (which have a 

so-called ‘heavy weight’ main fitting 

installed) or, respectively, with a P/N 

201456001 or P/N 201461001 (which are socalled ‘heavy weight’ NLG units) cancels the 

need for repetitive inspection and/or rework. 

The ‘heavy weight’ main fitting was 

originally developed for an increased weight 

version (101,000 lbs. maximum take-off 

weight) of the Fokker 100, as well as for the 

Fokker 70 (F28 Mark 0070), and introduced 

on the production line. 

M–D issued Service Bulletin (SB) F100– 

32–94 and Fokker Services issued SBF100– 

32–119, which provide instructions to install 

the P/N 201071003 or P/N 201071004 NLG 

on aeroplanes in service. In addition, Fokker 

Services issued optional SBF100–32–149 to 

introduce the P/N 201456001 or P/N 

201461001 NLG units on aeroplanes in 

service. 

In January 2010, a second NLG main fitting 

failure occurred. The results of the 

investigation showed that the fracture started 

from small fatigue cracks in the affected area. 

Prompted by this new occurrence, combined 

with the NLG certification methodology (safe 

life principle), EASA has decided that the 

existing terminating action, installation of a 

P/N 201071003 or P/N 201071004 NLG 

should be made mandatory. Alternatively, a 

P/N 201456001 or P/N 201461001 NLG can 

be installed, which meets the same 

requirement. 

For the reasons described above, EASA 

issued AD 2012–0002, retaining the 

requirements of [the Netherlands] AD * * *, 

which was superseded, and to require the 

replacement of all P/N 201071001 and P/N 

201071002 NLG units with, respectively, P/ 

N 201071003 and P/N 201071004 NLG units, 

or alternatively with, respectively, P/N 

201456001 or P/N 201461001 NLG units. 

Replacement of a NLG main fitting or of a 

NLG unit on an aeroplane constitutes 

terminating action for the repetitive 

inspections for that aeroplane. 

EASA AD 2012–0002 also prohibits, after 

modification of an aeroplane, installation of 

a P/N 201071001 or P/N 201071002 NLG unit 

on that aeroplane. 

* * * * * 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0062- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 11351, February 28, 2014) or on the 

determination of the cost to the public. 

‘‘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 11351, February 

28, 2014), we proposed to prevent the 

use of repairs that were not specifically 

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Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 70455 

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 11351, February 28, 2014) 

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 Fokker 

Services B.V.’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. 

Clarification of Language in Paragraph 

(m)(2) of This AD 

In paragraph (m)(2) of the NPRM (79 

FR 11351, February 28, 2014), we 

specified to contact certain aviation 

authorities ‘‘for instructions and follow 

those instructions.’’ As part of the 

change described previously regarding 

‘‘Contacting the Manufacturer’’ 

language, this text has been revised in 

paragraph (m)(2) of this AD to specify 

doing a repair using a method approved 

by the FAA, EASA, or Fokker Services 

B.V.’s EASA DOA. 

Conclusion 

We reviewed the available data 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 NPRM (79 FR 

11351, February 28, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 11351, 

February 28, 2014). 

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 4 

airplanes of U.S. registry. 

The actions required by AD 2000–17– 

03, Amendment 39–11876 (65 FR 

52298, August 29, 2000), and retained in 

this AD take about 2 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost $0 

per product. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2000–17–03 is $170 per 

product. 

We also estimate that it will take 

about 8 work-hours per product to 

comply with the new basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $525,000 

per product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $2,102,720, or $526,680 

per product. 

We have received no definitive data 

that would enable us to provide a cost 

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70456 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

estimate for the on-condition actions 

specified in this AD. 

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-2014-0062; 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) 

2000–17–03, Amendment 39–11876 (65 

FR 52298, August 29, 2000), and adding 

the following new AD: 

2014–23–09 Fokker Services B.V.: 

Amendment 39–18025. Docket No. 

FAA–2014–0062; Directorate Identifier 

2012–NM–031–AD. 

(a) Effective Date 

This AD becomes effective December 31, 

2014. 

(b) Affected ADs 

This AD replaces AD 2000–17–03, 

Amendment 39–11876 (65 FR 52298, August 

29, 2000). 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0100 airplanes; certificated 

in any category; all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a report of a 

nose landing gear (NLG) main fitting failure. 

We are issuing this AD to prevent cracking 

of the NLG main fitting, which could lead to 

collapse of the NLG during takeoff and 

landing, and possible injury to the flight crew 

and passengers. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained One-Time Detailed Visual 

Inspection 

This paragraph restates the actions 

required by paragraph (a) of AD 2000–17–03, 

Amendment 39–11876 (65 FR 52298, August 

29, 2000). For airplanes equipped with a 

Messier-Dowty NLG having part number 

(P/N) 201071001 or 201071002, on which a 

main fitting subassembly (MFSA) having 

P/N 201071200, 201071228, 201071248, or 

201071249 is installed: Prior to the 

accumulation of 7,500 total flight cycles or 

within 50 flight cycles after October 3, 2000 

(the effective date of AD 2000–17–03), 

whichever occurs later, perform a one-time 

detailed visual inspection of the NLG main 

fitting subassembly to detect cracking, in 

accordance with Part 1 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–118, dated 

October 8, 1999. 

(1) If no cracking is detected, no further 

action is required by this paragraph. 

(2) If any cracking is detected, prior to 

further flight, accomplish the actions 

required by paragraph (i) of this AD. 

(h) Definition of a Detailed Visual Inspection 

For the purposes of this AD, a detailed 

visual inspection is defined as: An intensive 

visual examination of a specific structural 

area, system, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at 

intensity deemed appropriate by the 

inspector. Inspection aids such as mirrors, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required. 

(i) Retained Repetitive Eddy Current and/or 

Dye Penetrant Inspections 

This paragraph restates the actions 

required by paragraph (b) of AD 2000–17–03, 

Amendment 39–11876 (65 FR 52298, August 

29, 2000), with a new exception. For 

airplanes equipped with a Messier-Dowty 

NLG having P/N 201071001 or 201071002, 

on which a MFSA having P/N 201071200, 

201071228, 201071248, or 201071249 is 

installed: Except as required by paragraph 

(g)(2) of this AD, prior to the accumulation 

of 7,875 total flight cycles, or within 375 

flight cycles after October 3, 2000 (the 

effective date of AD 2000–17–03), whichever 

occurs later, perform an eddy current or dye 

penetrant inspection of the NLG main fitting 

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subassembly to detect cracking, in 

accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–118, dated 

October 8, 1999. Such inspection within the 

compliance time required by the introductory 

text of paragraph (g) of this AD terminates the 

requirements of paragraph (g) of this AD. 

Repeat the inspection thereafter, using an 

eddy current or dye penetrant technique, at 

intervals not to exceed 750 flight cycles, 

except as required by paragraph (m)(1) of this 

AD. Repeat the inspection until the 

replacement specified in paragraph (l) of this 

AD is done, or the installation specified in 

paragraph (n) of this AD is done. 

(j) Retained Rework of Main Fitting 

This paragraph restates the actions 

required by paragraph (c) of AD 2000–17–03, 

Amendment 39–11876 (65 FR 52298, August 

29, 2000), with revised repair methods. If any 

cracking is detected during any inspection 

required by paragraph (g) or (i) of this AD: 

Prior to further flight, rework the main fitting 

of the NLG, in accordance with Part 3 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–118, dated 

October 8, 1999. If, after rework, any cracking 

remains that exceeds the limits specified in 

Fokker Service Bulletin SBF100–32–118, 

dated October 8, 1999, prior to further flight, 

accomplish the actions specified by either 

paragraph (j)(1) or (j)(2) of this AD. 

(1) Replace the NLG in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–118, dated 

October 8, 1999; and within 7,875 flight 

cycles after such replacement, perform the 

inspection as specified in paragraph (i) of 

this AD, and repeat the inspection thereafter 

at intervals not to exceed 750 flight cycles. 

(2) Repair in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the 

Rijksluchtvaartdienst (RLD) (or its delegated 

agent); or the European Aviation Safety 

Agency (EASA); or Fokker B.V. Service’s 

EASA Design Organization Approval (DOA). 

Note 1 to paragraph (j) of this AD: Fokker 

Service Bulletin SBF100–32–118, dated 

October 8, 1999, references Messier-Dowty 

Service Bulletin F100–32–92, Revision 1, 

dated October 8, 1999, as an additional 

source of service information for 

accomplishing the inspections and rework of 

the NLG main fitting subassembly. 

(k) Retained Reporting Requirements 

This paragraph restates the actions 

required by paragraph (d) of AD 2000–17–03, 

Amendment 39–11876 (65 FR 52298, August 

29, 2000), with revised contact information 

and minor editorial changes. Submit a report 

of the detailed visual inspection findings 

(positive and negative) required by paragraph 

(g) of this AD, and a report of the initial eddy 

current or dye penetrant inspection findings 

(positive and negative) required by paragraph 

(i) of this AD, to Fokker Services B.V., P.O. 

Box 231, 2150 AE Nieuw-Vennep, the 

Netherlands; or to Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com; at the applicable 

time specified in paragraph (k)(1) or (k)(2) of 

this AD. As of the effective date of this AD, 

submit reports to Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. 

(1) For airplanes on which the detailed 

visual inspection specified by paragraph (g) 

of this AD, and the initial repetitive eddy 

current or dye penetrant inspection specified 

by paragraph (i) of this AD, are accomplished 

after October 3, 2000 (the effective date of AD 

2000–17–03, Amendment 39–11876 (65 FR 

52298, August 29, 2000)): Submit each report 

within 7 days after performing the applicable 

inspection. 

(2) For airplanes on which the detailed 

visual inspection specified by paragraph (g) 

of this AD, and the initial repetitive eddy 

current or dye penetrant inspection specified 

in paragraph (i) of this AD, have been 

accomplished prior to October 3, 2000 (the 

effective date of AD 2000–17–03, 

Amendment 39–11876 (65 FR 52298, August 

29, 2000)): Submit the reports within 7 days 

after October 3, 2000 (the effective date of AD 

2000–17–03). 

(l) New Requirement of This AD: 

Replacement 

Except as provided by paragraph (m) of 

this AD, before the next scheduled main 

fitting overhaul of the NLG after the effective 

date of this AD, or within 36 months after the 

effective date of this AD, whichever occurs 

first: Replace all NLG units having P/N 

201071001 with a new P/N 201071003 NLG 

unit, and replace all NLG units having P/N 

201071002 with a new P/N 201071004 NLG 

unit, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–119, Revision 1, 

dated November 15, 2011, including Fokker 

Manual Change Notification MCNM–F100– 

043, dated January 31, 2000. 

(m) New Compliance Time Extension and 

On-Condition Actions 

For airplanes on which the next scheduled 

main fitting overhaul of the NLG is to occur 

later than 36 months after the effective date 

of this AD: Operators may accomplish the 

replacement required by paragraph (l) of this 

AD before the next scheduled main fitting 

overhaul of the NLG after the effective date 

of this AD, or within 72 months after the 

effective date of this AD, whichever occurs 

first, provided the actions specified in 

paragraphs (m)(1) and (m)(2) of this AD are 

done. 

(1) Within 36 months after the effective 

date of this AD, accomplish the inspection 

specified in paragraph (i) of this AD within 

750 flight cycles since the most recent 

inspection, and repeat thereafter at intervals 

not to exceed 375 flight cycles until the 

replacement specified in paragraph (l) of this 

AD is done or the installation specified in 

paragraph (n) of this AD is done. 

(2) In addition to the inspection specified 

in paragraph (m)(1) of this AD, do all other 

on-condition actions specified in paragraph 

1.E(1)(b) of Fokker Service Bulletin SBF100– 

32–119, Revision 1, dated November 15, 

2011, including Fokker Manual Change 

Notification MCNM–F100–043, dated 

January 31, 2000; except where Fokker 

Service Bulletin SBF100–32–119, Revision 1, 

dated November 15, 2011, including Fokker 

Manual Change Notification MCNM–F100– 

043, dated January 31, 2000, specifies to 

contact Fokker Services B.V., before further 

flight, repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Fokker Services B.V.’s EASA 

Design Organization Approval (DOA). 

Note 2 to paragraph (m) of this AD: Fokker 

Service Bulletin SBF100–32–119, Revision 1, 

dated November 15, 2011, including Fokker 

Manual Change Notification MCNM–F100– 

043, dated January 31, 2000, references 

Messier-Dowty Service Bulletin F100–32–94, 

dated January 5, 2000, as an additional 

source of service information for replacing 

the NLG unit. 

(n) New Optional Action 

Installing a new P/N 201456001 or P/N 

201461001 NLG unit, in accordance with 

Fokker Proforma Service Bulletin SBF100– 

32–149, Revision 1, dated October 25, 2007, 

including Appendix 1, dated December 12, 

2006, is acceptable for compliance with the 

replacement required by paragraph (l) of this 

AD, provided the installation is 

accomplished within the compliance time 

specified in paragraph (l) of this AD; and, 

except for airplanes that comply with 

paragraph (m) of this AD, provided the 

installation is accomplished within the 

compliance time specified in paragraph (m) 

of this AD. 

(o) New Requirement: Concurrent 

Modification 

Prior to, or concurrently with, the 

installation of the NLG unit required by 

paragraph (l) of this AD or the optional 

installation specified in paragraph (n) of this 

AD, modify the NLG bracket, in accordance 

with the Accomplishment Instructions of 

Fokker Service Bulletin SBF100–53–074, 

dated November 1, 1999. 

(p) New Terminating Actions 

Accomplishing the replacement specified 

in paragraph (l) of this AD or the installation 

specified in paragraph (n) of this AD 

terminates the repetitive eddy current or dye 

penetrant inspections required by paragraphs 

(i) and (m)(1) of this AD. 

(q) New Parts Installation Prohibition 

(1) For airplanes equipped with a MessierDowty NLG having P/N) 201071001 or 

201071002, on which a main fitting 

subassembly (MFSA) having P/N 201071200, 

201071228, 201071248, or 201071249 is 

installed: As of October 3, 2000 (the effective 

date of AD 2000–17–03, Amendment 39– 

11876 (65 FR 52298, August 29, 2000), and 

until the effective date of this AD, no person 

may install an NLG having P/N 201071001 or 

201071002 unless the installed MFSA has 

been inspected by means of an eddy current 

or dye penetrant inspection, and corrected in 

accordance with paragraph (i) of this AD. 

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70458 Federal Register / Vol. 79, No. 228 / Wednesday, November 26, 2014 / Rules and Regulations 

(2) For all airplanes: As of the effective 

date of this AD, no person may install an 

NLG having P/N 201071001 or 201071002 on 

any airplane. 

(r) Credit for Previous Actions 

This paragraph provides credit for the 

replacement required by paragraph (l) of this 

AD, if those actions were performed before 

the effective date of this AD using Fokker 

Service Bulletin SBF 100–32–119, dated 

January 31, 2000, provided P/N 201071003 or 

201071004 nose gear has been installed. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: 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 Fokker Services B.V.’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. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0002R1, dated 

March 30, 2012, for related information. You 

may examine the MCAI in the AD docket on 

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

#!documentDetail;D=FAA-2014-0062-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (u)(5) and (u)(6) of this AD. 

(u) 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) Fokker Service Bulletin SBF 100–32– 

119, Revision 1, dated November 15, 2011, 

including Fokker Manual Change 

Notification MCNM–F100–043, dated 

January 31, 2000. 

(ii) Fokker Proforma Service Bulletin SBF 

100–32–149, Revision 1, dated October 25, 

2007, including Appendix 1, dated December 

12, 2006. 

(iii) Fokker Service Bulletin SBF 100–53– 

074, dated November 1, 1999. 

(4) The following service information was 

approved for IBR on October 3, 2000 (65 FR 

52298, August 17, 2000). 

(i) Fokker Service Bulletin SBF100–32– 

118, dated October 8, 1999. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.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. 2014–27361 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–2014–0425; Directorate 

Identifier 2013–NM–180–AD; Amendment 

39–18024; AD 2014–23–08] 

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) 2012–06– 

19 for certain Airbus Model A330–201, 

–202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and 

–343 airplanes; and Model A340–200 

and –300 series airplanes. AD 2012–06– 

19 required repetitive inspections of the 

main fitting and sliding tube of the nose 

landing gear (NLG) for defects, damage, 

and cracks; and corrective actions if 

necessary. This new AD requires an 

inspection of the part number and serial 

number of the NLG main fitting and 

NLG sliding tube; for affected parts, this 

new AD requires a magnetic particle 

inspection (MPI) for cracks, and flap 

peening and replacement if necessary. 

This new AD also requires, for certain 

parts, additional inspections for damage 

and cracking. This new AD also adds 

airplanes to the applicability. This AD 

was prompted by reports of a cracked 

main fitting and sliding tube during 

NLG overhaul. We are issuing this AD 

to detect and correct cracks, defects, or 

damage of the main fitting or sliding 

tube, which could result in consequent 

NLG collapse. 

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 April 30, 2012 (77 FR 

22188, April 13, 2012). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0425; 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. 

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