Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules 11351 

instructions for submitting comments. If 

you submit your comment to the 

Federal eRulemaking Portal, please also 

send it by email to FHFA at 

RegComments@fhfa.gov to ensure 

timely receipt by FHFA. Include the 

following information in the subject line 

of your submission: Comments/RIN 

2590–AA59. 

• Email: Comments to Alfred M. 

Pollard, General Counsel may be sent by 

email to RegComments@fhfa.gov. Please 

include ‘‘RIN 2590–AA59’’ in the 

subject line of the message. 

• U.S. Mail, United Parcel Service, 

Federal Express, or Other Mail Service: 

The mailing address for comments is: 

Alfred M. Pollard, General Counsel, 

Attention: Comments/RIN 2590–AA59, 

Federal Housing Finance Agency, 

Eighth Floor (OGC), 400 Seventh Street 

SW., Washington, DC 20024. 

• Hand Delivered/Courier: The hand 

delivery address is: Alfred M. Pollard, 

General Counsel, Attention: Comments/ 

RIN 2590–AA59, Federal Housing 

Finance Agency, Eighth Floor (OGC), 

400 7th Street SW., Washington, DC 

20024. The package should be logged at 

the Guard Desk, First Floor, on business 

days between 9 a.m. and 5 p.m. 

FOR FURTHER INFORMATION CONTACT: 

Amy Bogdon, Amy.Bogdon@fhfa.gov, 

(202) 649–3320, Associate Director, 

Division of Federal Home Loan Bank 

Regulation; or Michou Nguyen, 

Michou.Nguyen@fhfa.gov, (202) 649– 

3081 (not toll-free numbers), Assistant 

General Counsel, Office of General 

Counsel, Federal Housing Finance 

Agency, Constitution Center, Eighth 

Floor (OGC), 400 7th Street SW., 

Washington, DC 20024. The telephone 

number for the Telecommunications 

Device for the Hearing Impaired is (800) 

877–8339. 

SUPPLEMENTARY INFORMATION: On 

January 28, 2014, FHFA published for 

comment in the Federal Register a 

proposed rule, and invited public 

comments. See 79 FR 4414. The 

comment period for the proposed rule is 

scheduled to close on March 31, 2014 

(the 60th day after the date of 

publication). In response to requests 

from the Federal Home Loan Banks for 

additional time to review the proposed 

rule and provide comments, FHFA is 

extending the comment period for 45 

days, changing the deadline for 

submitting comments on the proposed 

rule to May 15, 2014. 

Dated: February 24, 2014. 

Melvin L. Watt, 

Director, Federal Housing Finance Agency. 

[FR Doc. 2014–04421 Filed 2–27–14; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0062; Directorate 

Identifier 2012–NM–031–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2000–17– 

03 that applies to all Fokker Services 

B.V. Model F.28 Mark 0100 airplanes. 

AD 2000–17–03 currently requires a 

one-time visual inspection and 

repetitive eddy current and dye 

penetrant inspections of the nose 

landing gear (NLG) main fitting to detect 

cracking of the NLG main fitting 

subassembly, and corrective actions if 

necessary. Since we issued AD 2000– 

17–03, we were advised that 

replacement of certain nose landing gear 

(NLG) units eliminates the need for 

repetitive inspections. This proposed 

AD would retain existing requirements, 

require installation a new part number 

NLG unit that would terminate the 

repetitive inspections, and add 

airplanes to the applicability. We are 

proposing 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: We must receive comments on 

this proposed AD by April 14, 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: 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 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 by searching for 

and locating Docket No. 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 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–2014–0062; Directorate Identifier 

2012–NM–031–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 August 17, 2000, we issued AD 

2000–17–03, Amendment 39–11876 (65 

FR 52298, August 29, 2000). AD 2000– 

17–03 requires actions intended to 

address an unsafe condition on Fokker 

Services B.V. Model F.28 Mark 0100 

airplanes. 

Since we issued AD 2000–17–03, 

Amendment 39–11876 (65 FR 52298, 

August 29, 2000), we received a report 

of a NLG main fitting failure. The 

European Aviation Safety Agency 


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11352 Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules 

(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 

for the specified products. 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 AD (BLA) 

1997–116 (currently at issue 2) to require 

repetitive inspections of the NLG main fitting 

and, depending on findings, rework or 

replacement of the NLG main fitting. 

Since AD (BLA) 1997–116/2 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 CAA–NL AD (BLA) 1997– 

116/2, 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. 

* * * * * 

This proposed AD expands the 

applicability to include all Fokker 

Services B.V. Model F.28 Mark 0100 

airplanes. 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– 

2014–0062. 

Relevant Service Information 

Fokker Services B.V. has issued the 

following service bulletins: 

• Fokker Services B.V. Service 

Bulletin SBF 100–32–119, Revision 1, 

dated November 15, 2011, which refers 

to 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. 

• Fokker Services B.V. Service 

Bulletin Change Notification SBF 100– 

32–119/1, dated January 31, 2000. 

• Fokker Services B.V. Proforma 

Service Bulletin SBF 100–32–149, 

Revision 1, dated October 25, 2007, 

including Appendix 1, dated December 

12, 2006. 

• Fokker Services B.V. Service 

Bulletin SBF 100–53–074, dated 

November 1, 1999. 

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. 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, certain 

requirements of this proposed AD 

specify that the repair approval 

specifically refer to the FAA AD. This 

change is 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 use the phrase ‘‘its 

delegated agent, or the DAH with State 

of Design Authority design organization 

approval, as applicable’’ in this 

proposed AD to refer to a DAH 

authorized to approve certain required 

repairs for this proposed AD. 

Explanation of Changes Made to the 

Existing AD 

On July 10, 2002, the FAA issued a 

new version of 14 CFR part 39 (67 FR 

47997, July 22, 2002), which governs the 

FAA’s airworthiness directives system. 

The regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance (AMOCs). Because we 

have now included this material in 14 

CFR part 39, only the office authorized 


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to approve AMOCs is identified in each 

individual AD. Therefore, Notes 1 and 

5 of AD 2000–17–03, Amendment 39– 

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

are not included in this NPRM. We have 

also revised Note 2 of AD 2000–17–03 

to lettered paragraph (h) in this NPRM 

(this change does not affect the intent of 

that Note) and removed Note 3 of that 

AD because that information does not 

apply to the new actions specified in 

this NPRM. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 airplanes of U.S. registry. 

The actions that are required by AD 

2000–17–03, Amendment 39–11876 (65 

FR 52298, August 29, 2000), and 

retained in this proposed AD take about 

2 work-hours 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 2000–17–03 is $170 per 

product. 

We also estimate that it would take 

about 8 work-hours per product to 

comply with the new basic 

requirements of this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about 

$525,000 per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed there will be no charge 

for these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this 

proposed 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 

estimate for the on-condition actions 

specified in this proposed 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 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. Amend § 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: 

Fokker Services B.V.: Docket No. FAA– 

2014–0062; Directorate Identifier 2012– 

NM–031–AD. 

(a) Comments Due Date 

We must receive comments by April 14, 

2014. 

(b) Affected ADs 

This AD supersedes 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 reports of nose 

landing gear (NLG) main fitting failures. 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 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 

Messier-Dowty nose landing gear (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. 


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11354 Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules 

(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 Messier-Dowty nose 

landing gear (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: 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 subassembly to detect 

cracking, in accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–118, dated 

October 8, 1999 (which is incorporated by 

reference in AD 2000–17–03). Such 

inspection within the compliance time 

required by 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 (which is incorporated by 

reference in AD 2000–17–03). 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 (which is incorporated by 

reference in AD 2000–17–03); 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 (or its delegated agent, or the Design 

Approval Holder with EASA’s design 

organization approval, as applicable). For a 

repair method to be approved by the 

Manager, International Branch, ANM–116, as 

required by this paragraph, the Manager’s 

approval letter must specifically reference 

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

FR 52298, August 29, 2000). For a repair 

method to be approved as of the effective 

date of this AD, the repair approval must 

specifically refer to this AD. 

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

Service Bulletin SBF100–32–118, dated 

October 8, 1999 (which is incorporated by 

reference in AD 2000–17–03), 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 nose landing gear 

(NLG) after the effective date of this AD, or 

within 36 months after the effective date of 

this AD, whichever occurs first: Replace all 

nose landing gear (NLG) units having part 

number (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 

Services Bulletin SBF100–32–119, Revision 

1, dated November 15, 2011. 

(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 nose landing gear (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 Services Bulletin SBF100– 

32–119, Revision 1, dated November 15, 

2011, except where Fokker Services Bulletin 

SBF100–32–119, Revision 1, dated November 

15, 2011, specifies to contact Fokker 

Services, before further flight, contact either 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA (or its delegated agent, or the Design 

Approval Holder with EASA’s design 

organization approval, as applicable) for 

instructions and follow those instructions. 

For a repair method to be approved, the 

repair approval must specifically refer to this 

AD. 

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

Service Bulletin SBF100–32–119, Revision 1, 

dated November 15, 2011, 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 the 

Fokker Service Bulletin SBF100–32–149, 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 40 / Friday, February 28, 2014 / Proposed Rules 11355 

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 nose landing gear (NLG) 

bracket, in accordance with the 

Accomplishment Instructions of Fokker 

Services Bulletin SBF100–53–074, Revision 

1, dated October 25, 2007. 

(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 MessierDowty nose landing gear (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: 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. 

(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 

Services B.V. Service Bulletin SBF 100–32– 

119, dated January 31, 2000, provided part 

number 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) 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 DAH with a State 

of Design Authority’s design organization 

approval). 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. 

(t) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2012–0002R1, dated March 30, 

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– 

2014–0062. 

(2) 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. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04499 Filed 2–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0123; Directorate 

Identifier 2013–NM–040–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, -B4–605R, B4–622R, 

-F4–605R, F4–622R, and -C4–605R 

Variant F airplanes; and Model A310– 

203, –204, –221, –222, –304, –322, –324, 

and –325 airplanes. This proposed AD 

was prompted by a report of inner skin 

disbonding damage on a rudder. This 

proposed AD would require repetitive 

ultrasonic inspections for disbonding of 

certain rudders; an elasticity of laminate 

checker inspection; a woodpecker or tap 

test inspection; venting the core, if 

necessary; and repairing, if necessary. 

We are proposing this AD to detect and 

correct rudder disbonding, which could 

affect the structural integrity of the 

rudder. 

DATES: We must receive comments on 

this proposed AD by April 14, 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 Airbus SAS, 


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