Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56601 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 

millimeters (mm), before further flight, 

remove the restraining tab, clamp the 

restraining tab (F) in a vice with soft jaws, 

and gradually apply a load (H) to ensure a 

clearance of 3 mm or more, as depicted in 

Figure 1, Detail K of ASB 67A007. 

(2) For Model SA–365N, SA–365N1, AS– 

365N2, and AS 365 N3 helicopters: 

(i) Completely loosen the friction, lock the 

collective pitch lever, and using a spring 

scale, measure the load (G) required to 

unlock the pilot’s collective pitch lever as 

depicted in Figure 1, Detail B of Eurocopter 

ASB No. 67.00.10, Revision 1, dated February 

25, 2009 (ASB 67.00.10). 

(ii) If the collective pitch lever unlocks at 

a load less than 5 daN (11.3 lbs) or greater 

than 14 daN (31.5 lbs), before further flight, 

adjust the collective pitch lever restraining 

tab (F) using the oblong holes and adjust the 

collective link rods as described in the 

Accomplishment Instructions, paragraph 

2.B.4., of ASB 67.00.10. 

(iii) Set the collective pitch lever to the 

‘‘low pitch’’ position and hold it in this 

position, without forcing it downwards. 

(iv) Tighten the friction lock and measure 

the clearance (J1) between the locking pin of 

the collective pitch lever (C) and the Lsection of the restraining tab (F) as depicted 

in Figure 1, Detail A of ASB 67.00.10. 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 mm, 

before further flight, remove the restraining 

tab, clamp the restraining tab (F) in a vice 

with soft jaws, and gradually apply a load (H) 

to ensure a clearance of 3 mm or more, as 

depicted in Figure 1, Detail K, of ASB 

67.00.10. 

(3) For Model SA–366G1 helicopters: 

(i) Completely loosen the friction, lock the 

collective pitch lever, and using a spring 

scale, measure the load (G) required to 

unlock the pilot’s collective pitch lever as 

depicted in Figure 1, Detail B of Eurocopter 

ASB No. 67.05, Revision 1, dated February 

25, 2009 (ASB 67.05). 

(ii) If the collective pitch lever unlocks at 

a load less than 5 daN (11.3 lbs) or greater 

than 14 daN (31.5 lbs), before further flight, 

adjust the collective pitch lever restraining 

tab (F) using the oblong holes and adjust the 

collective link rods as described in the 

Accomplishment Instructions, paragraph 

2.B.4., of ASB 67.05. 

(iii) Set the collective pitch lever to the 

‘‘low pitch’’ position and hold it in this 

position, without forcing it downwards. 

(iv) Tighten the friction lock and measure 

the clearance (J1) between the locking pin of 

the collective pitch lever (C) and the Lsection of the restraining tab (F) as depicted 

in Figure 1, Detail A, of ASB 67.05. 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 mm, 

before further flight, remove the restraining 

tab, clamp the restraining tab (F) in a vice 

with soft jaws, and gradually apply a load (H) 

to ensure a clearance of 3 mm or more, as 

depicted in Figure 1, Detail K, of ASB 67.05. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matt.wilbanks@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

(1) Eurocopter Alert Service Bulletin (ASB) 

No. 67.00.12, Revision 0, dated February 25, 

2009; ASB No. 67.07, Revision 0, dated 

February 25, 2009; and ASB No. 67–009, 

Revision 1, dated July 19, 2010, which are 

not incorporated by reference, contain 

additional information about this AD. For 

service information identified in this AD, 

contact American Eurocopter Corporation, 

2701 N. Forum Drive, Grand Prairie, TX 

75052; telephone (972) 641–0000 or (800) 

232–0323; fax (972) 641–3775; or at http://

www.eurocopter.com/techpub. You may 

review a copy of the service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2011–0154, dated August 22, 2011. You 

may view the EASA AD in the AD Docket on 

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

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710: Main Rotor Control 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin No. 

67.00.10, Revision 1, dated February 25, 

2009. 

(ii) Eurocopter Alert Service Bulletin No. 

67.05, Revision 1, dated February 25, 2009. 

(iii) Eurocopter Alert Service Bulletin No. 

67A007, Revision 1, dated February 25, 2009. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may also 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 Fort Worth, Texas, on August 21, 

2013. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–22170 Filed 9–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0270; Directorate 

Identifier 2011–NM–113–AD; Amendment 

39–17570; AD 2013–17–06] 

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 adopting a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.27 Mark 

050 airplanes, and Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by reports of loose nuts on 

contactors in the electrical power center 

(EPC), and in some cases, burned 

contactors. This AD requires inspecting 

and, if necessary, adjusting, the torque 

values of nuts on circuit breakers, 

contactors, and terminal blocks of the 

EPC and battery relay panel. This AD 

also requires inspecting to determine if 

certain parts are installed, and installing 

the parts if necessary. We are issuing 

this AD to detect and correct loose nuts, 

which could result in arcing and 

potentially an onboard fire, possibly 

resulting in damage to the airplane and 

injury to occupants or maintenance 

personnel. 

DATES: This AD becomes effective 

October 18, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 18, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 


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56602 Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an AD 

that would apply to the specified 

products. The SNPRM published in the 

Federal Register on February 5, 2013 

(78 FR 8058). We preceded the SNPRM 

with a notice of proposed rulemaking 

(NPRM), which published in the 

Federal Register on March 21, 2012 (77 

FR 16486). The NPRM and the SNPRM 

both proposed to correct an unsafe 

condition for the specified products. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, issued EASA 

Airworthiness Directive 2012–0050, 

dated March 27, 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 December 1989, Fokker issued Service 

Bulletin (SB) SBF50–24–A013 and SBF100– 

24–A011 (both Alert Bulletins) to instruct 

operators to inspect and adjust several torque 

values of bus bars and contactors in the EPC. 

The Civil Aviation Authority of The 

Netherlands (CAA–NL, formerly RLD) issued 

AD (BLA) 89–159 and BLA 89–157 

respectively (both now at issue 2), to require 

operators of the affected aeroplanes to 

comply with the instructions of these SB’s. 

Since those [Dutch] ADs were issued, 

several operators reported finding loose nuts 

on contactors in the EPC of Fokker 50/60 

aeroplanes in post-SBF50–24–A013 

configuration and on Fokker 70/100 

aeroplanes in post-SBF100–24–A011 

configuration. In some cases, the findings 

included damaged (burned) contactors. 

This condition, if not detected and 

corrected, could lead to arcing and, in 

combination with other factors, to an onboard fire, possibly resulting in damage to 

the aeroplane and injury to occupants or 

maintenance personnel. EASA issued AD 

2011–0083 [referenced in the earlier FAA 

NPRM (77 FR 16486, March 21, 2012)] to 

address this unsafe condition. 

After that [EASA] AD was issued, it was 

noticed that terminal block TB4906A, used in 

some Fokker 100 aeroplanes, was missing 

from the list of affected terminal blocks, as 

specified in Fokker SBF100–24–043. To 

correct this oversight, Fokker Services issued 

Revision 1 of SBF100–24–043, adding 

terminal block TB4906A. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0083, which is superseded, and for 

F28 Mark 0100 aeroplanes, adds required 

action for the missing terminal block 

TB4906A by making reference to SBF100– 

24–043 Revision 1. 

The required actions include doing a 

general visual inspection to determine if 

either the lock washer, flat washer and 

nut, or locking nut and flat washer are 

installed; installing a new lock washer 

or self-locking nut, if necessary; and 

applying torque inspection lacquer. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(78 FR 8058, February 5, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (78 FR 

8058, February 5, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (78 FR 8058, 

February 5, 2013). 

Costs of Compliance 

We estimate that this AD will affect 

about 4 products of U.S. registry. We 

also estimate that it will take about 5 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $1,700, or $425 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 4 work-hours and require parts 

costing $25, for a cost of $365 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the MCAI, 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: 


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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56603 

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 adding 

the following new AD: 

2013–17–06 Fokker Services B.V.: 

Amendment 39–17570. Docket No. 

FAA–2012–0270; Directorate Identifier 

2011–NM–113–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 18, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Fokker Services B.V. 

Model F.27 Mark 050 airplanes, and Model 

F.28 Mark 0070 and 0100 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electric power. 

(e) Reason 

This AD was prompted by reports of loose 

nuts on contactors in the electrical power 

center (EPC), and in some cases, burned 

contactors. We are issuing this AD to detect 

and correct loose nuts, which could result in 

arcing and potentially an onboard fire, 

possibly resulting in damage to the airplane 

and injury to occupants or maintenance 

personnel. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Actions 

Within 24 months after the effective date 

of this AD, do the actions specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

(1) Do a torque check of the nuts and 

circuit breakers, contactors, and terminal 

blocks of the EPC and battery relay panel, as 

applicable; and do all applicable adjustments 

of the torque values; in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF50–24–032, dated 

February 10, 2011 (for Model F.27 Mark 050 

airplanes); or the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–24–043, Revision 1, dated December 

15, 2011 (for Model F.28 Mark 0070 and 0100 

airplanes). Do all applicable adjustments 

before further flight. 

(2) Do a general visual inspection of the 

contacts and nuts on circuit breakers, 

contactors, and terminal blocks of the EPC 

and battery relay panel to determine if either 

the lock washer, flat washer and nut, or 

locking nut and flat washer are installed; and 

do all applicable installations; in accordance 

with the Accomplishment Instructions of 

Fokker Service Bulletin SBF50–24–032, 

dated February 10, 2011 (for Model F.27 

Mark 050 airplanes); or the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–24–043, Revision 1, dated December 

15, 2011 (for Model F.28 Mark 0070 and 0100 

airplanes). Do all applicable installations 

before further flight. 

(3) Before further flight, after 

accomplishing any check required by 

paragraph (g)(1) of this AD or any inspection 

required by paragraph (g)(2) of this AD: 

Apply torque inspection lacquer, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF50–24–032, dated February 10, 2011 (for 

Model F.27 Mark 050 airplanes); or the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–24–043, Revision 1, 

dated December 15, 2011 (for Model F.28 

Mark 0070 and 0100 airplanes). 

(h) 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, Washington 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 or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0050, dated March 27, 2012, 

for related information, which can be found 

in the AD docket on the Internet at http://

www.regulations.gov. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Fokker Service Bulletin SBF50–24–032, 

dated February 10, 2011. 

(ii) Fokker Service Bulletin SBF100–24– 

043, Revision 1, dated December 15, 2011. 

(3) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

16, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–21672 Filed 9–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

PENSION BENEFIT GUARANTY 

CORPORATION 

29 CFR Parts 4022 and 4044 

Allocation of Assets in SingleEmployer Plans; Benefits Payable in 

Terminated Single-Employer Plans; 

Interest Assumptions for Valuing and 

Paying Benefits 

AGENCY: Pension Benefit Guaranty 

Corporation. 

ACTION: Final rule. 

SUMMARY: This final rule amends the 

Pension Benefit Guaranty Corporation’s 

regulations on Benefits Payable in 

Terminated Single-Employer Plans and 

Allocation of Assets in Single-Employer 

Plans to prescribe interest assumptions 

under the benefit payments regulation 

for valuation dates in October 2013 and 

interest assumptions under the asset 

allocation regulation for valuation dates 

in the fourth quarter of 2013. The 

interest assumptions are used for 

valuing and paying benefits under 

terminating single-employer plans 

covered by the pension insurance 

system administered by PBGC. 

DATES: Effective October 1, 2013. 

FOR FURTHER INFORMATION CONTACT: 

Catherine B. Klion (Klion.Catherine@

PBGC.gov), Assistant General Counsel 

for Regulatory Affairs, Pension Benefit 

Guaranty Corporation, 1200 K Street 


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