Federal Register / Vol. 75, No. 223 / Friday, November 19, 2010 / Proposed Rules 70861 

25.175(b)(1), 25.177(a) through (c), and 

25.181 must be met, is the lower of: 

* * * * * 

Issued in Washington, DC, on November 9, 

2010. 

KC Yanamura, 

Deputy Director, Aircraft Certification 

Service. 

[FR Doc. 2010–29193 Filed 11–18–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1114; Directorate 

Identifier 2010–NM–206–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 0100, 

1000, 2000, 3000, and 4000 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Prompted by an accident * * *, the FAA 

published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. The design review 

conducted by Fokker on the F28 in response 

to these regulations revealed that, in case of 

a lightning strike, an ignition source can 

develop in the wing tank vapour space 

during fuel transfer from bag tank CWT 

[center wing tank], if the electrical power for 

refuelling is not switched off after refuelling. 

Service experience has revealed situations 

where the power switch of the Fuelling 

Control Panel (FCP) appeared to be ‘‘ON’’ 

with the access panel closed. The cam on the 

access panel that should operate the power 

switch, if forgotten by flight crew or 

maintenance staff, can pivot away during 

closing of the panel, which may result in the 

switch staying in the ‘‘ON’’ position. 

This condition, if not corrected, could 

result in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by January 3, 2011. 

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 W12–40, 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 231, 2150 AE Nieuw-Vennep, 

the Netherlands; telephone +31 (0)252– 

627–350; fax +31 (0)252–627–211; 

e-mail technicalservices.fokkerservices@

stork.com; Internet http://www.

myfokkerfleet.com. You may review 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington. 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 Operations office 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, 

Washington 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–2010–1114; Directorate Identifier 

2010–NM–206–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 EASA 

Airworthiness Directive 2010–0139, 

dated July 1, 2010 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Prompted by an accident * * *, the FAA 

published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. The design review 

conducted by Fokker on the F28 in response 

to these regulations revealed that, in case of 

a lightning strike, an ignition source can 

develop in the wing tank vapour space 

during fuel transfer from bag tank CWT 

[center wing tank], if the electrical power for 

refuelling is not switched off after refuelling. 

Service experience has revealed situations 

where the power switch of the Fuelling 

Control Panel (FCP) appeared to be ‘‘ON’’ 

with the access panel closed. The cam on the 

access panel that should operate the power 

switch, if forgotten by flight crew or 

maintenance staff, can pivot away during 

closing of the panel, which may result in the 

switch staying in the ‘‘ON’’ position. 

This condition, if not corrected, could 

result in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires an inspection of the cam 

and, depending on findings, replacement 

with an improved part. Subsequently, this 

AD requires repetitive functional checks of 

the cam and, depending on findings, the 

necessary corrective actions. 

The corrective action is adjusting the 

FCP cam until it operates correctly. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Fokker Services B.V. has issued 

Fokker Service Bulletins SBF28–28– 

052, dated April 20, 2010; and SBF100– 

28–063, dated April 15, 2010. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
70862 Federal Register / Vol. 75, No. 223 / Friday, November 19, 2010 / Proposed Rules 

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. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 6 products of U.S. registry. 

We also estimate that it would take 

about 3 work-hours 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 $426 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. 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 the 

proposed AD on U.S. operators to be 

$4,086, or $681 per product. 

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); and 

3. 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 proposed AD and placed it in the 

AD docket. 

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 adding 

the following new AD: 

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

2010–1114; Directorate Identifier 2010– 

NM–206–AD. 

Comments Due Date 

(a) We must receive comments by January 

3, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Services B.V. 

Model F28 Mark 1000, 2000, 3000, and 4000 

airplanes, all serial numbers, equipped with 

a center wing tank (CWT); and Model F28 

Mark 0100 airplanes, serial numbers 11244 

through 11441; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Prompted by an accident * * *, the FAA 

published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. The design review 

conducted by Fokker on the F28 in response 

to these regulations revealed that, in case of 

a lightning strike, an ignition source can 

develop in the wing tank vapour space 

during fuel transfer from bag tank CWT 

[center wing tank], if the electrical power for 

refuelling is not switched off after refuelling. 

Service experience has revealed situations 

where the power switch of the Fuelling 

Control Panel (FCP) appeared to be ‘‘ON’’ 

with the access panel closed. The cam on the 

access panel that should operate the power 

switch, if forgotten by flight crew or 

maintenance staff, can pivot away during 

closing of the panel, which may result in the 

switch staying in the ‘‘ON’’ position. 

This condition, if not corrected, could 

result in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

Initial Inspection and Corrective Actions 

(g) Within 6 months after the effective date 

of this AD, inspect the FCP cam to determine 

the part number (P/N), in accordance with 

Part 1 of the Accomplishment Instructions of 

Fokker Service Bulletin SBF28–28–052, 

dated April 20, 2010 (for Model F28 Mark 

1000, 2000, 3000, and 4000 airplanes); or 

SBF100–28–063, dated April 15, 2010 (for 

Model F28 Mark 0100 airplanes). 

(1) If the correct part number is installed 

(P/N D48127–009 for Model F28 Mark 0100 

airplanes and P/N A42509–089 for Model 

F28 Mark 1000, 2000, 3000, and 4000 

airplanes), before further flight, do an 

inspection to verify that the cam operates 

correctly, in accordance with Part 1 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–052, dated April 

20, 2010 (for Model F28 Mark 1000, 2000, 

3000, and 4000 airplanes); or SBF100–28– 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 223 / Friday, November 19, 2010 / Proposed Rules 70863 

063, dated April 15, 2010 (for Model F28 

Mark 0100 airplanes). 

(2) If a part number other than P/N 

D48127–009 for Model F28 Mark 0100 

airplanes and P/N A42509–089 for Model 

F28 Mark 1000, 2000, 3000, and 4000 

airplanes is installed, within 24 months after 

the effective date of this AD, replace the cam 

with a cam having a correct part number, and 

do an inspection to verify that the cam 

operates correctly, in accordance with Part 2 

of the Accomplishment Instructions of 

Fokker Service Bulletin SBF28–28–052, 

dated April 20, 2010 (for Model F28 Mark 

1000, 2000, 3000, and 4000 airplanes); or 

SBF100–28–063, dated April 15, 2010 (for 

Model F28 Mark 0100 airplanes). 

(3) If, during any inspection required by 

paragraphs (g)(1) and (g)(2) of this AD, the 

cam does not operate correctly, before further 

flight, adjust the cam until it operates 

correctly, in accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–052, dated April 

20, 2010 (for Model F28 Mark 1000, 2000, 

3000, and 4000 airplanes); or SBF100–28– 

063, dated April 15, 2010 (for Model F28 

Mark 0100 airplanes). 

Repetitive Inspections 

(h) Within 1,200 flight hours after verifying 

that the cam operates correctly, as required 

by paragraphs (g)(1) and (g)(2) of this AD, as 

applicable: Do an inspection to verify that the 

cam operates correctly and, before further 

flight, do all applicable corrective actions, in 

accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–052, dated April 

20, 2010 (for Model F28 Mark 1000, 2000, 

3000, and 4000 airplanes); or SBF100–28– 

063, dated April 15, 2010 (for Model F28 

Mark 0100 airplanes). Thereafter, repeat the 

inspection of the cam at intervals not to 

exceed 1,200 flight hours. 

Parts Installation 

(i) As of the effective date of this AD, no 

person may install an FCP access door, cam, 

or fueling panel on any airplane, unless the 

requirements of this AD have been 

accomplished on the cam. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although paragraph (6) of the MCAI provides 

an option to incorporate the repetitive 

functional inspection into the maintenance 

program and then use the maintenance 

program as a method of complying with the 

repetitive inspection requirement, this AD 

does not include that provision. 

Other FAA AD Provisions 

(j) 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. 

Send information 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. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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 FAAapproved 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. 

(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. 

Related Information 

(k) Refer to MCAI EASA Airworthiness 

Directive 2010–0139, dated July 1, 2010; 

Fokker Service Bulletin SBF28–28–052, 

dated April 20, 2010; and Fokker Service 

Bulletin SBF100–28–063, dated April 15, 

2010; for related information. 

Issued in Renton, Washington, on 

November 10, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–29228 Filed 11–18–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0090; Directorate 

Identifier 2007–NM–312–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Model 747 airplanes. The 

original NPRM would have required 

measuring the electrical bond resistance 

between the motor operated valve 

(MOV) actuators and airplane structure 

for the main, center, auxiliary, and 

horizontal stabilizer fuel tanks, as 

applicable, and corrective action if 

necessary. The original NPRM also 

would have required a revision to the 

maintenance program to incorporate 

airworthiness limitation (AWL) No. 28– 

AWL–21 or AWL No. 28–AWL–27, as 

applicable. The original NPRM resulted 

from fuel system reviews conducted by 

the manufacturer. This supplemental 

NPRM would revise the original NPRM 

by adding airplanes to the applicability, 

and would require replacing 

production-installed laminate phenolic 

spacers with metallic spacers between 

the fuel jettison MOV and the airplane 

structure, as applicable. We are 

proposing this supplemental NPRM to 

prevent electrical current from flowing 

through an MOV actuator into a fuel 

tank, which could create a potential 

ignition source inside the fuel tank. This 

condition, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

DATES: We must receive comments on 

this supplemental NPRM by December 

14, 2010. 

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 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 


emcdonald on DSK2BSOYB1PROD with PROPOSALS