Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 6541 

the compliance times specified, unless the 

actions have already been done. 

Initial Inspections and Replacement/Repair 

(g) For airplanes that have accumulated 

4,000 or less total flight hours as of the 

effective date of this AD: Before the 

accumulation of 6,000 total flight hours, do 

a detailed inspection of the RTL for broken 

return springs and damage through the 

casing, or chafing of the casing of the primary 

actuator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–055, Revision A, 

dated August 6, 2010. Before further flight, 

replace any broken return springs with new 

springs, and repair or replace with a new 

actuator any chafed or damaged primary 

actuator, as applicable, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–27–055, 

Revision A, dated August 6, 2010. Repeat the 

inspection thereafter at intervals not to 

exceed 6,000 flight hours. 

(h) For airplanes that have accumulated 

more than 4,000 total flight hours as of the 

effective date of this AD: Within 2,000 flight 

hours after the effective date of this AD, do 

a detailed inspection of the RTL for broken 

return springs and damage through the 

casing, or chafing of the casing of the primary 

actuator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–055, Revision A, 

dated August 6, 2010. Before further flight, 

replace any broken return springs with new 

springs, and repair or replace any chafed or 

damaged primary actuator with a new 

actuator, as applicable, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–27–055, 

Revision A, dated August 6, 2010. Repeat the 

inspection thereafter at intervals not to 

exceed 6,000 flight hours. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 670BA–27–055, 

dated May 11, 2010, are considered 

acceptable for compliance with the 

corresponding actions specified in this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. 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. 

Related Information 

(k) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–18, dated June 16, 2010; 

and Bombardier Service Bulletin 670BA–27– 

055, Revision A, dated August 6, 2010; for 

related information. 

Material Incorporated by Reference 

(l) You must use Bombardier Service 

Bulletin 670BA–27–055, Revision A, dated 

August 6, 2010, to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

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/

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2443 Filed 2–4–11; 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; Amendment 

39–16591; AD 2011–03–07] 

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), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This 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. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 14, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 14, 2011. 

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 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
6542 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 

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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 19, 2010 (75 FR 

70861). That NPRM proposed 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM 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. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 6 

products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will 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 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 AD 

to the 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 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 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); 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 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 the NPRM, 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–03–07 Fokker Services B.V.: 

Amendment 39–16591. Docket No. 

FAA–2010–1114; Directorate Identifier 

2010–NM–206–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 14, 2011. 

Affected ADs 

(b) None. 

Applicability 

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

Model F.28 Mark 1000, 2000, 3000, and 4000 

airplanes, all serial numbers, equipped with 

a center wing tank (CWT); and Model F.28 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 6543 

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. 

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 F.28 Mark 

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

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

Model F.28 Mark 0100 airplanes). 

(1) If the correct part number is installed 

(P/N D48127–009 for Model F.28 Mark 0100 

airplanes and P/N A42509–089 for Model 

F.28 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 F.28 Mark 1000, 2000, 

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

063, dated April 15, 2010 (for Model F.28 

Mark 0100 airplanes). 

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

D48127–009 for Model F.28 Mark 0100 

airplanes and P/N A42509–089 for Model 

F.28 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 F.28 Mark 

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

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

Model F.28 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 F.28 Mark 1000, 2000, 

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

063, dated April 15, 2010 (for Model F.28 

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 F.28 Mark 1000, 2000, 

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

063, dated April 15, 2010 (for Model F.28 

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, 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. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency (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. 

Material Incorporated by Reference 

(l) You must use Fokker Service Bulletin 

SBF28–28–052, dated April 20, 2010; or 

Fokker Service Bulletin SBF100–28–063, 

dated April 15, 2010; as applicable; to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) 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; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2162 Filed 2–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0852; Directorate 

Identifier 2010–NM–005–AD; Amendment 

39–16594; AD 2011–03–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 and A340–200 and 

–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1