This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

63439

Vol. 69, No. 211

Tuesday, November 2, 2004

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18787; Directorate 

Identifier 2003–NM–264–AD; Amendment 

39–13837; AD 2004–22–09] 

RIN 2120–AA64

Airworthiness Directives; Fokker 

Model F27 Mark 100, 200, 300, 400, 500, 

600, and 700 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Fokker Model F27 Mark 100, 200, 300, 

400, 500, 600, and 700 series airplanes. 

This AD requires a one-time highfrequency eddy current inspection for 

cracking of the attachment lugs of the 

aileron spring tab balance unit, and 

corrective actions if necessary. This AD 

is prompted by a report indicating that, 

during heavy turbulence, a pilot needed 

to apply aileron trim to maintain level 

flight because cracking of the upper 

inboard attachment lug of the aileron 

spring tab balance unit, probably due to 

corrosion, had caused permanent 

deflection of the spring tab and 

consequent aileron damage. We are 

issuing this AD to prevent diminished 

control of the airplane in turbulence or 

total loss of roll control for the affected 

wing.

DATES: This AD becomes effective 

December 7, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of December 7, 2004.

ADDRESSES: For service information 

identified in this AD, contact Fokker 

Services B.V., P.O. Box 231, 2150 AE 

Nieuw-Vennep, The Netherlands. You 

can examine this information 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. 

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Room PL–401, on the plaza level 

of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: 

Technical information: Tom 

Rodriguez, Aerospace Engineer; 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov. 

Examining the Docket 

The AD docket contains the proposed 

AD, comments, and any final 

disposition. You can examine the AD 

docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the DOT street address stated in the 

ADDRESSES section.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

an AD for all Fokker Model F27 Mark 

100, 200, 300, 400, 500, 600, and 700 

series airplanes. The proposed AD was 

published in the Federal Register on 

August 6, 2004 (69 FR 47806), to require 

a one-time high-frequency eddy current 

inspection for cracking of the 

attachment lugs of the aileron spring tab 

balance unit, and corrective actions if 

necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been submitted on the proposed 

AD or on the determination of the cost 

to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

This AD will affect about 38 airplanes 

of U.S. registry. The actions will take 

about 5 work hours per airplane, at an 

average labor rate of $65 per work hour. 

Based on these figures, the estimated 

cost of the AD for U.S. operators is 

$12,350, or $325 per airplane. 

Regulatory Findings 

We have 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 

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. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation.

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.

63440 Federal Register / Vol. 69, No. 211 / Tuesday, November 2, 2004 / Rules and Regulations 

§ 39.13 [Amended]

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive:

2004–22–09 Fokker Services B.V.:

Amendment 39–13837. Docket No. 

FAA–2004–18787; Directorate Identifier 

2003–NM–264–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 7, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Fokker Model 

F27 Mark 100, 200, 300, 400, 500, 600, and 

700 series airplanes; certificated in any 

category. 

Unsafe Condition 

(d) This AD was prompted by a report 

indicating that, during heavy turbulence, a 

pilot needed to apply aileron trim to 

maintain level flight because cracking of the 

upper inboard attachment lug of the aileron 

spring tab balance unit, probably due to 

corrosion, had caused permanent deflection 

of the spring tab and consequent aileron 

damage. We are issuing this AD to prevent 

diminished control of the airplane in 

turbulence or total loss of roll control for the 

affected wing. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection 

(f) Within 24 months after the effective 

date of this AD, perform a one-time highfrequency eddy current inspection for 

cracking of the attachment lugs of the aileron 

spring tab balance units by doing all the 

actions in the Accomplishment Instructions 

of Fokker Service Bulletin F27/27–137, dated 

March 19, 2003. If no loose paint, corrosion 

damage, or crack is found during this 

inspection, no further action is required by 

this AD. 

Repair and Rework of Attachment Lugs 

(g) If no crack is found during the 

inspection required by paragraph (f) of this 

AD, but it was necessary to remove loose 

paint or corrosion to perform the inspection: 

Prior to further flight, rework the attachment 

lugs in accordance with the Accomplishment 

Instructions of Fokker Service Bulletin F27/

27–137, dated March 19, 2003. If corrosion 

damage has caused any attachment lug to 

exceed the dimensional limits specified in 

the service bulletin: Prior to further flight, 

replace the aileron spring tab balance unit 

with a serviceable unit, in accordance with 

the Accomplishment Instructions of Fokker 

Service Bulletin F27/27–137, dated March 

19, 2003, or repair the lug in accordance with 

a method approved by the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the Civil 

Aviation Authority—The Netherlands (CAA–

NL) (or its delegated agent). 

Replacement 

(h) If any crack is found during the 

inspection required by paragraph (f) of this 

AD: Prior to further flight, replace the aileron 

spring tab balance unit with a serviceable 

unit, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin F27/27–137, dated March 

19, 2003. 

No Reporting Requirement 

(i) Although Fokker Service Bulletin F27/

27–137, dated March 19, 2003, specifies to 

submit certain information to Fokker 

Services B.V., this AD does not include such 

a requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(j) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Related Information 

(k) Dutch airworthiness directive 2003–

037, dated March 31, 2003, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(l) You must use Fokker Service Bulletin 

F27/27–137, dated March 19, 2003, to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approves the 

incorporation by reference of this document 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. For copies of the service information, 

contact Fokker Services B.V., P.O. Box 231, 

2150 AE Nieuw-Vennep, The Netherlands. 

For information on the availability of this 

material at the National Archives and 

Records Administration (NARA), call (202) 

741–6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. You may view the AD 

docket at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW., Room PL–401, Nassif 

Building, Washington, DC.

Issued in Renton, Washington, on October 

19, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–24221 Filed 11–1–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2004–SW–03–AD; Amendment 

39–13841; AD 2004–22–13] 

RIN 2120–AA64

Airworthiness Directives; Bell 

Helicopter Textron Canada Model 

206L–1 and 206L–3 Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Bell Helicopter Textron 

Canada (Bell) model helicopters that 

requires a one-time inspection of the 

adjustable stop screws of the magnetic 

brake assembly; repairing, as 

appropriate, certain mechanical damage 

to the cyclic and collective flight control 

magnetic brake arm assembly (arm 

assembly), if necessary; and installing 

the stop screw with the proper adhesive, 

adjusting the arm assembly travel and 

applying slippage marks. This 

amendment is prompted by reports that 

the magnetic brake adjustable screws 

have backed out, which limited travel of 

the arm assembly. The actions specified 

by this AD are intended to detect loose 

adjustable stop screws, that could result 

in limiting the travel of the cyclic and 

collective arm assembly, and 

subsequent loss of control of the 

helicopter.

DATES: Effective December 7, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

7, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Bell Helicopter Textron Canada, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272. 

This information may be examined at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas; or 

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.

FOR FURTHER INFORMATION CONTACT:

Charles Harrison, Aviation Safety