6106 Federal Register / Vol. 79, No. 22 / Monday, February 3, 2014 / Proposed Rules 

THSA within 12 months or 1,500 flight 

cycles after the effective date of this AD, 

whichever occurs first. 

(2) For a THSA that has accumulated 

16,000 total flight cycles or more, but less 

than 20,000 total flight cycles since the 

THSA’s first installation on an airplane, as of 

the effective date of this AD, and that is 

installed on an Airbus Model A330–201, 

–202, –203, –223, –223F, –243, –243F, –301, 

–302, –303, –321, –322, –323, –341, –342, or 

–343 airplane: Replace the THSA within 30 

months or 4,000 flight cycles after the 

effective date of this AD, whichever occurs 

first. 

(3) For a THSA that has accumulated 

16,000 total flight cycles or more, but less 

that 20,000 total flight cycles since the 

THSA’s first installation on an airplane, as of 

the effective date of this AD, and that is 

installed on an Airbus Model A340–211, 

–212, –213, –311, –312, or –313 airplane: 

Replace the THSA within 30 months or 3,000 

flight cycles after the effective date of this 

AD, whichever occurs first. 

(i) Definition of Serviceable THSA 

Except as required by paragraph (j)(2) of 

this AD, for the purposes of this AD a 

serviceable THSA is a THSA: 

(1) Having a part number identified in 

Airbus AOT A27L005–13, dated July 11, 

2013, that has accumulated fewer than 

20,000 total flight cycles since first 

installation on an airplane; or 

(2) Having a part number that is not 

identified in Airbus AOT A27L005–13, dated 

July 11, 2013. 

(j) Parts Installation Limitation and 

Replacement 

(1) As of 12 months after the effective date 

of this AD, no person may install on any 

airplane a THSA with a part number 

specified in Airbus AOT A27L005–13, dated 

July 11, 2013, that has accumulated 20,000 

total flight cycles or more since the THSA’s 

first installation on an airplane. For any 

airplane having a THSA with a part number 

specified in Airbus AOT A27L005–13, dated 

July 11, 2013, that has accumulated 20,000 

total flight cycles or more since the THSA’s 

first installation on an airplane: As of 12 

months after the effective date of this AD, 

before further flight, replace the affected 

THSA with a serviceable THSA, in 

accordance with Airbus AOT A27L005–13, 

dated July 11, 2013. 

(2) As of 30 months after the effective date 

of this AD, no person may install on any 

airplane a THSA with a part number 

specified in Airbus AOT A27L005–13, dated 

July 11, 2013, that has accumulated 16,000 

total flight cycles or more since the THSA’s 

first installation on an airplane. For any 

airplane having a THSA with a part number 

specified in Airbus AOT A27L005–13, dated 

July 11, 2013, that has accumulated 16,000 

total flight cycles or more since the THSA’s 

first installation on an airplane: As of 30 

months after the effective date of this AD, 

before further flight, replace the affected 

THSA with a serviceable THSA, in 

accordance with Airbus AOT A27L005–13, 

dated July 11, 2013. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

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

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the Design 

Approval Holder with a State of Design 

Authority’s design organization approval). 

For a repair method to be approved, the 

repair approval must specifically refer to this 

AD. You are required to ensure the product 

is airworthy before it is returned to service. 

(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. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0144R1, dated August 27, 

2013, for related information. This MCAI 

may be found in the AD docket on the 

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

searching for and locating it in Docket No. 

FAA–2014–0006. 

(2) 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 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. 

Issued in Renton, Washington, on January 

22, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02156 Filed 1–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0008; Directorate 

Identifier 2013–NM–076–AD] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2012–23– 

09, for all Embraer S.A. Model ERJ 190– 

100 STD, –100 LR, and –100 IGW 

airplanes; and Model ERJ 190–200 STD, 

–200 LR, and –200 IGW airplanes. AD 

2012–23–09 currently requires revising 

the maintenance program to incorporate 

modifications in airworthiness 

limitations specified in Embraer S.A. 

ERJ 190 195 Maintenance Review Board 

Report (MRBR). Since we issued AD 

2012–23–09, we have determined that 

more restrictive maintenance 

requirements and airworthiness 

limitations are necessary. This proposed 

AD would require revising the 

maintenance or inspection program to 

incorporate modifications in the 

airworthiness limitations specified in 

Embraer S.A. ERJ 190 195 MRBR to 

include new inspection tasks and their 

respective thresholds and intervals. We 

are proposing this AD to detect and 

correct fatigue cracking of structural 

components, which could result in 

reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by March 20, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 79, No. 22 / Monday, February 3, 2014 / Proposed Rules 6107 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Embraer S.A., 

Technical Publications Section (PC 

060), Av. Brigadeiro Faria Lima, 2170— 

Putim—12227–901 Sa ̃o Jose dos 

Campos—SP—BRASIL; telephone +55 

12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email distrib@

embraer.com.br; Internet http://

www.flyembraer.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0008; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kathrine Rask, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: (425) 227–2180; 

fax: (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0008; Directorate Identifier 

2013–NM–076–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On November 13, 2012, we issued AD 

2012–23–09, Amendment 39–17265 (77 

FR 73270, December 10, 2012). AD 

2012–23–09 requires actions intended to 

address an unsafe condition on the 

products listed above. 

Since we issued AD 2012–23–09, 

Amendment 39–17265 (77 FR 73270, 

December 10, 2012), the Ageˆncia 

Nacional de Aviac ̧a ̃o Civil (ANAC), 

which is the airworthiness authority for 

Brazil, has issued Brazilian 

Airworthiness Directive 2012–10–02, 

dated October 29, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’). We have determined that more 

restrictive maintenance requirements 

and airworthiness limitations are 

necessary. The MCAI states: 

This [Brazilian] AD (http://www2.anac.gov.

br/certificacao/da/textos/1363amd.pdf) 

results from a new revision to the 

Airworthiness Limitations Section (ALS) of 

Embraer ERJ 190 Maintenance Review Board 

Report (MRBR 1928), to include new or 

modification of the current tasks and its 

respective thresholds and intervals. Failure 

to inspect these structural components, 

according to the new or revised tasks, 

thresholds and intervals, could prevent a 

timely detection of fatigue cracking. These 

cracks, if not properly addressed, could 

adversely affect the structural integrity of the 

airplane. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0008. 

Relevant Service Information 

Embraer S.A. has issued Part 2— 

Airworthiness Limitation Inspections 

(ALI)—Structures, of Appendix A, 

Airworthiness Limitation—(AL), of the 

EMBRAER 190 195 MRBR, MRB–1928, 

Revision 6, dated August 20, 2012; and 

Temporary Revision (TR) 6–3, dated 

November 30, 2012, to Part 2— 

Airworthiness Limitation Inspections 

(ALI)—Structures, of Appendix A, 

Airworthiness Limitations—(AL), of the 

EMBRAER 190 195 MRBR, MRB–1928, 

Revision 6, dated August 20, 2012. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This AD requires revisions to certain 

operator maintenance documents to 

include new actions (e.g., inspections) 

and/or Critical Design Configuration 

Control Limitations (CDCCLs). 

Compliance with these actions and/or 

CDCCLs is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by this AD, the 

operator may not be able to accomplish 

the actions described in the revisions. In 

this situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance according to paragraph (k) 

of this AD. The request should include 

a description of changes to the required 

actions that will ensure the continued 

damage tolerance of the affected 

structure. 

Costs of Compliance 

We estimate that this proposed AD 

affects 98 airplanes of U.S. registry. 

The actions that are required by AD 

2012–23–09, Amendment 39–17265 (77 

FR 73270, December 10, 2012), and 

retained in this proposed AD take about 

1 work-hour per product, at an average 

labor rate of $85 per work-hour. 

Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2012–23–09 is $85 per 

product. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $8,330, or 85 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

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6108 Federal Register / Vol. 79, No. 22 / Monday, February 3, 2014 / Proposed Rules 

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 proposed 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

2012–23–09, Amendment 39–17265 (77 

FR 73270, December 10, 2012): 

Embraer S.A: Docket No. FAA–2014–0008; 

Directorate Identifier 2013–NM–076–AD. 

(a) Comments 

We must receive comments by March 20, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2012–23–09, 

Amendment 39–17265 (77 FR 73270, 

December 10, 2012). 

(c) Applicability 

This AD applies to Embraer S.A. Model 

ERJ 190–100 STD, –100 LR, and –100 IGW 

airplanes; and Model ERJ 190–200 STD, –200 

LR, and –200 IGW airplanes; certificated in 

any category; all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors; 53, Fuselage; 54, 

Nacelles/Pylons; 55, Stabilizers; 57, Wings; 

71, Powerplant; and 78, Engine Exhaust. 

(e) Reason 

This AD was prompted by a determination 

that more restrictive maintenance 

requirements and airworthiness limitations 

are necessary. We are proposing this AD to 

detect and correct fatigue cracking of 

structural components, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision of the Maintenance 

Program 

This paragraph restates the actions 

required by paragraph (h) of AD 2012–23–09, 

Amendment 39–17265 (77 FR 73270, 

December 10, 2012). Within 90 days after 

January 14, 2013 (the effective date of AD 

2012–23–09), revise the maintenance 

program to incorporate the tasks specified in 

Part 2—Airworthiness Limitation Inspections 

(ALI)—Structures, of Appendix A, 

Airworthiness Limitations (AL), of the 

EMBRAER 190 Maintenance Review Board 

Report, MRB–1928, Revision 5, dated 

November 11, 2010; and EMBRAER 

Temporary Revision (TR) 5–1, dated 

February 11, 2011, to Part 2—Airworthiness 

Limitation Inspections (ALI)—Structures, of 

Appendix A, Airworthiness Limitations (AL), 

of the EMBRAER 190 Maintenance Review 

Board Report, MRB–1928, Revision 5, dated 

November 11, 2010; with the thresholds and 

intervals stated in these documents. The 

initial compliance times for the tasks are 

stated in the ‘‘Implementation Plan’’ section 

of Appendix A, Airworthiness Limitations 

(AL), of the EMBRAER 190 Maintenance 

Review Board Report, MRB–1928, Revision 5, 

dated November 11, 2010. 

(h) Retained No Alternative Actions or 

Intervals 

This paragraph restates the actions 

required by paragraph (i) of AD 2012–23–09, 

Amendment 39–17265 (77 FR 73270, 

December 10, 2012). After accomplishing the 

revision required by paragraph (g) of this AD, 

no alternative actions (e.g., inspections) or 

intervals, may be used, unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (k)(1) of this AD, and except as 

required by paragraph (i) of this AD. 

(i) New Requirements of This AD: Revision 

of the Maintenance or Inspection Program 

Within 60 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

tasks specified in Part 2—Airworthiness 

Limitation Inspections (ALI)—Structures, of 

Appendix A, Airworthiness Limitations— 

(AL), of the EMBRAER 190 195 Maintenance 

Review Board Report MRB–1928, Revision 6, 

dated August 20, 2012; and EMBRAER TR 6– 

3, dated November 30, 2012, to Part 2— 

Airworthiness Limitation Inspections (ALI)— 

Structures, of Appendix A, Airworthiness 

Limitations—(AL), of the EMBRAER 190 195 

Maintenance Review Board Report, MRB– 

1928, Revision 6, dated August 20, 2012; 

with the thresholds and intervals stated in 

these documents. The initial compliance 

times for the tasks are stated in the 

‘‘Implementation Plan’’ section of Appendix 

A, Airworthiness Limitations—(AL), of the 

EMBRAER 190 195 Maintenance Review 

Board Report, MRB–1928, Revision 6, dated 

November 30, 2012, or within 90 days after 

the effective date of this AD, whichever 

occurs later. Doing the revision required by 

this paragraph terminates the revision 

required by paragraph (g) of this AD. 

(j) No Alternative Actions, Intervals, and/or 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After accomplishment of the revision 

required by paragraph (i) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and/or CDCCLs may be used unless 

the actions, intervals, and/or CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (k)(1) 

of this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Kathrine Rask, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: (425) 227–2180; 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/

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Federal Register / Vol. 79, No. 22 / Monday, February 3, 2014 / Proposed Rules 6109 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the Design Approval 

Holder with a State of Design Authority’s 

design organization approval, as applicable). 

For a repair method to be approved, the 

repair approval must specifically refer to this 

AD. You are required to ensure the product 

is airworthy before it is returned to service. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Brazilian 

Airworthiness Directive 2012–10–02, dated 

October 29, 2012, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2014–0008. 

(2) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; telephone 

+55 12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email distrib@

embraer.com.br; Internet http://

www.flyembraer.com. 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. 

Issued in Renton, Washington, on January 

22, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02159 Filed 1–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0007; Directorate 

Identifier 2012–NM–038–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This proposed 

AD was prompted by reports that the 

bracket of the rod in the carbon fiber 

reinforced plastic (CFRP) main landing 

gear (MLG) outboard door had detached. 

In addition, we received reports of 

broken recessed heads on titanium 

attachment bolts of the operating rod 

brackets on the modified CFRP MLG 

outboard doors. This proposed AD 

would require a detailed inspection of 

the CFRP MLG outboard door for play 

or cracks in the recessed countersunk 

heads of the operating rod bracket 

attachment bolts; replacement of the 

bolt if necessary; and, for certain 

airplanes, modification of the CFRP 

MLG outboard doors and attachment to 

the MLG. We are proposing this AD to 

detect and correct the affected MLG 

from moving to the down and locked 

position, which could result in MLG 

collapse during landing or roll-out, and 

consequent damage to the airplane and 

injury to passengers. 

DATES: We must receive comments on 

this proposed AD by March 20, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0007; Directorate Identifier 

2012–NM–038–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Airworthiness 

Directive 2012–0023, dated February 6, 

2012 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for the specified 

products. The MCAI states: 

In 2005, several occurrences were reported 

where the bracket of the rod in the Carbon 

Fibre Reinforced Plastic (CFRP) MLG 

outboard door had detached, preventing the 

MLG to lock properly when selected down. 

Prompted by these reports, CAA–NL [Civil 

Aviation Authority-Netherlands] issued AD 

NL–2006–001 (EASA approval 2006–0002) to 

require the inspection and modification of 

the attachment of the operating rod bracket 

as detailed in Fokker Service Bulletin (SB) 

SBF100–52–080. 

After that [EASA] AD was issued, several 

operators reported broken recessed heads of 

titanium attachment bolts of the operating 

rod bracket on modified (i.e. post-SBF100– 

52–080) CFRP MLG outboard doors. In such 

a situation, the remaining bolt shafts can get 

pulled through the external repair patch and 

the carbon fibre door outer skin, causing the 

operating rod, with the detached bracket, to 

get stuck between the MLG main fitting and 

wing lower skin. The primary factor to the 

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