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 

Federal Register / Vol. 69, No. 211 / Tuesday, November 2, 2004 / Rules and Regulations 63441

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Standards Staff, Fort Worth, 

Texas 76193–0110, telephone (817) 

222–5128, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for the specified model 

helicopters was published in the 

Federal Register on May 12, 2004 (69 

FR 26325). That action proposed to 

require within 100 hours time-in-service 

or within 90 days, whichever occurs 

first, and before installation of an 

affected magnetic brake, a one-time 

inspection of the adjustable stop screws 

of the magnetic brake assembly; 

repairing, as appropriate, certain 

mechanical damage to the arm 

assembly, if necessary; and installing 

the stop screw with the proper adhesive, 

adjusting the arm assembly travel and 

applying slippage marks. 

Transport Canada, the airworthiness 

authority for Canada, notified the FAA 

that an unsafe condition may exist on 

Bell Model 206L–1 and 206L–3 

helicopters with Instrument Flight Rule 

(IFR) Kit, part number (P/N) 206–705–

001, –101, or –103, installed, and all 

delivered spare magnetic brakes, P/N 

204–001–376–003, manufactured by 

Memcor Truohm, Inc. as P/N MP 498–

3. Transport Canada advises that the 

stop screws, P/N MS51959–3, of the 

magnetic brake, P/N 204–001–376–003 

(Memcor Truohm P/N MP 498–3), were 

installed without the proper adhesive. 

Bell has issued Alert Service Bulletin 

(ASB) No. 206L–01–122, dated October 

3, 2001, which specifies a one-time 

inspection of the magnetic brake 

adjustable stop screw, P/N MS51959–3; 

repairing any arm assembly mechanical 

damage created by the screws; and 

installing the stop screw with the proper 

adhesive and adjusting the arm 

assembly shaft travel. Transport Canada 

classified this alert service bulletin as 

mandatory and issued AD No. CF–

2002–16, dated March 4, 2002, to ensure 

the continued airworthiness of these 

helicopters in Canada. 

These helicopter models are 

manufactured in Canada and are type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. Pursuant to the applicable 

bilateral agreement, Transport Canada 

has kept the FAA informed of the 

situation described above. The FAA has 

examined the findings of Transport 

Canada, reviewed all available 

information, and determined that AD 

action is necessary for products of these 

type designs that are certificated for 

operation in the United States. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. The FAA has 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed. 

The FAA estimates that 577 

helicopters of U.S. registry will be 

affected by this AD, that it will take 

approximately 3 work hours per 

helicopter to accomplish the required 

actions, and that the average labor rate 

is $65 per work hour. Required parts 

will cost approximately $3,785. Based 

on these figures, the total cost impact of 

this AD on U.S. operators is estimated 

to be $298,500, assuming that 75 

helicopters in the U.S. will require the 

actions described in this AD. 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows:

2004–22–13 Bell Helicopter Textron 

Canada: Amendment 39–13841. Docket 

No. 2004–SW–03–AD.

Applicability: Model 206L–1 and 206L–3 

helicopters with Instrument Flight Rule (IFR) 

Kit, part number (P/N) 206–705–001, –101, or 

–103, and a magnetic brake, P/N 204–001–

376–003, manufactured by Memcor Truohm, 

Inc. (M.T. Inc.) as P/N MP 498–3, installed, 

certificated in any category. 

Compliance: Required within 100 hours 

time-in-service or 90 days, whichever occurs 

first, and before installation of any affected 

magnetic brake, unless accomplished 

previously. 

To detect loose adjustable stop screws, 

which could result in limiting the travel of 

the cyclic and collective arm assembly, and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Inspect and, if necessary, repair, adjust, 

and apply slippage marks to the magnetic 

brake assembly by following the 

Accomplishment Instructions, paragraphs 6. 

through 12., in Bell Helicopter Textron Alert 

Service Bulletin (ASB) No. 206L–01–122, 

dated October 3, 2001, except if damage to 

the arm assembly exceeds 0.030 inch (0.762 

mm), replace the magnetic brake assembly 

with an airworthy magnetic brake assembly. 

Contacting the manufacturer is not required. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Safety Management Group, 

Rotorcraft Directorate, FAA, for information 

about previously approved alternative 

methods of compliance. 

(c) The inspection and, if necessary, the 

modification shall be done in accordance 

with Bell Helicopter Textron Alert Service 

Bulletin No. 206L–01–122, dated October 3, 

2001. The Director of the Federal Register 

approved this incorporation by reference in 

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

part 51. Copies 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. Copies may be inspected 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.

(d) This amendment becomes effective on 

December 7, 2004.

Note: The subject of this AD is addressed 

in Transport Canada (Canada) AD No. CF–

2002–16, dated March 4, 2002.

63442 Federal Register / Vol. 69, No. 211 / Tuesday, November 2, 2004 / Rules and Regulations 

Issued in Fort Worth, Texas, on October 22, 

2004. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service.

[FR Doc. 04–24225 Filed 11–1–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–SW–39–AD; Amendment 

39–13839; AD 2004–22–11] 

RIN 2120–AA64

Airworthiness Directives; Eurocopter 

Deutschland GmbH Model EC135 P1, 

P2, T1, and T2 Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for Eurocopter Deutschland GmbH 

(Eurocopter) Model EC135 P1, P2, T1, 

and T2 helicopters. That AD currently 

requires adding the AD or a statement 

to the Rotorcraft Flight Manual (RFM) 

informing the pilot to reduce power and 

land as soon as practicable if a thumplike sound followed by an unusual 

vibration occurs during flight. That AD 

also requires visually inspecting the 

main rotor drive torque strut assembly 

(strut) for a crack or a break, recording 

the inspections in the historical or 

equivalent record, re-marking and 

relocating the strut, as appropriate, and 

replacing any unairworthy strut with an 

airworthy strut. Also, that AD 

establishes life limits for certain struts 

and revises the life limit for other struts. 

This amendment requires the same 

actions as the existing AD except that it 

changes the visual inspection from a 

one-time inspection to daily 

inspections; reduces the life limit for 

aluminum struts; and eliminates the 

once-only transfer and remarking of 

certain struts. This amendment is 

prompted by an incident in which a 

pilot felt an in-flight increase in 

vibration and subsequent discovery of a 

failed strut. The actions specified by 

this AD are intended to prevent failure 

of a strut 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 American Eurocopter Corporation, 

2701 Forum Drive, Grand Prairie, Texas 

75053–4005, telephone (972) 641–3460, 

fax (972) 641–3527. 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:

Richard Monschke, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Standards Staff, Fort Worth, 

Texas 76193–0110, telephone (817) 

222–5116, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 by 

superseding AD 2003–20–11, 

Amendment 39–13329 (68 FR 58581, 

October 10, 2003), for the specified 

Eurocopter model helicopters was 

published in the Federal Register on 

June 2, 2004 (69 FR 31051). The action 

proposed to require adding the AD or a 

statement to the RFM informing the 

pilot to reduce power and land as soon 

as practicable if a thump-like sound 

followed by unusual vibration occurs 

during flight; visually inspecting the 

strut for a crack or a break before the 

first flight of each day; replacing any 

unairworthy strut with an airworthy 

strut; replacing all aluminum struts with 

titanium struts on or before 

accumulating 500 hours time-in service 

(TIS) or no later than December 31, 

2004, whichever occurs first; installing 

the struts in pairs; and canceling the 

once-only transfer and remarking of 

certain struts. 

The Luftfahrt-Bundesamt (LBA), the 

airworthiness authority for the Federal 

Republic of Germany, notified the FAA 

that an unsafe condition may exist on 

Eurocopter Model EC135 P1, P2, T1, 

and T2 helicopters. The LBA advises 

that the holders of affected aircraft 

registered in the Federal Republic of 

Germany must carry out the inspection 

for a crack, marking, replacement, and 

reduction of life limit of struts in 

accordance with the manufacturer’s 

alert service bulletin. 

Eurocopter has issued Alert Service 

Bulletin EC135–63A–002, Revision 4, 

dated July 7, 2003 (ASB), concerning 

reduction in life limit for the strut, and 

visual inspections of the strut and 

emergency stop. The ASB contains 

errors—in paragraph 1.A., the 

abbreviation ‘‘S/N’’ should be ‘‘P/N’’

and in paragraphs 1.C., 1.E.(1), and 

1.E.(2), it incorrectly states that the ASB 

is Revision 3 rather than Revision 4. The 

LBA classified this ASB as mandatory 

and issued AD No. 2001–107/3, dated 

August 21, 2003, to ensure the 

continued airworthiness of these 

helicopters in the Federal Republic of 

Germany. 

These helicopter models are 

manufactured in Germany and are type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. Pursuant to the applicable 

bilateral agreement, the LBA has kept 

the FAA informed of the situation 

described above. The FAA has 

examined the findings of the LBA, 

reviewed all available information, and 

determined that AD action is necessary 

for products of this type design that are 

certificated for operation in the United 

States. 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were received on the 

proposal or the FAA’s determination of 

the cost to the public. The FAA has 

determined that air safety and the 

public interest require the adoption of 

the rule as proposed with only a minor 

editorial change. This change will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

The FAA estimates that this AD will 

affect 50 helicopters of U.S. registry. It 

will take approximately 92.25 work 

hours per helicopter to accomplish the 

inspections and parts replacement at an 

average labor rate of $65 per work hour. 

Required parts will cost approximately 

$7,296 per helicopter. Based on these 

figures, we estimate the total cost 

impact of this AD on U.S. operators to 

be $664,612 to replace the aluminum 

struts on the entire fleet. 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132.

For the reasons discussed above, I 

certify that this action (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