63054 Federal Register / Vol. 69, No. 209 / Friday, October 29, 2004 / Rules and Regulations 

§ 39.13 [Amended]

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive:

2004–22–03 Empresa Brasileira de 

Aeonautica S.A. (EMBRAER):

Amendment 39–13831. Docket No. 

FAA–2004–18582; Directorate Identifier 

2003–NM–35–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 3, 2004. 

Affected ADs 

(b) None.

Applicability: (c) This AD applies to 

EMBRAER Model EMB–135 and –145 series 

airplanes, as listed in EMBRAER Service 

Bulletin 145–57–0034, Change 01, dated 

January 9, 2002; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a report 

indicating that trunnion fittings of the wings 

have been manufactured with a web fillet 

radius smaller than the minimum required by 

the design data, which may induce the 

occurrence of fatigue cracks at the root of the 

trunnion fillet radius and adjacent structures 

(e.g., spar and ribs). We are issuing this AD 

to detect and correct fatigue cracking of the 

wing trunnion fittings or adjacent structure, 

which could result in failure of the main 

landing gear, consequent damage to 

surrounding structure, and possible loss of 

control of the airplane during landing. 

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. 

Service Bulletin 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of EMBRAER Service Bulletin 

145–57–0034, Change 01, dated January 9, 

2002. 

Measurement 

(g) Before the accumulation of 2,000 total 

flight cycles, or within 500 flight hours after 

the effective date of this AD, whichever 

occurs later, measure the fillet radius 

dimension of the trunnion fitting webs of the 

wings in accordance with paragraph 3.(C), 

‘‘Part I,’’ of the service bulletin. 

(1) If the fillet radius value is equal to or 

greater than 0.1969 inches (5 mm), no further 

action is required by this AD. 

(2) If a fillet radius value is less than 

0.0394 inches (1 mm), before further flight, 

do the actions specified in paragraph (h) of 

this AD. 

(3) If the fillet radius value is equal to or 

greater than 0.0394 inch (1 mm), but less 

than 0.1969 inch (5 mm), before the 

accumulation of 4,000 total flight cycles, or 

within 500 flight hours after the effective 

date of this AD, whichever occurs later, do 

the actions specified in paragraph (h) of this 

AD. 

Rework and Further Corrective Actions, if 

Necessary 

(h) Rework the fillet radius of the trunnion 

fitting web to increase the radius, do related 

investigative actions, and do applicable 

corrective actions by accomplishing all the 

actions specified in paragraph 3.(D), ‘‘Part 

II,’’ of the service bulletin. Do the actions in 

accordance with the service bulletin, except 

as provided by paragraph (i) of this AD. Any 

applicable corrective actions must be done 

before further flight. 

(1) If the final fillet radius is less than 

0.1969 inch (5 mm) and the radius limit 

contour is reached, before further flight, 

repair in accordance with a method approved 

by either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Departmento de Aviacao 

Civil (DAC) (or its delegated agent). 

(2) If the final fillet radius is equal to or 

greater than 0.1969 inches (5 mm), before 

further flight, shot-peen the reworked area in 

accordance with paragraph 3.(E), ‘‘Part III,’’

of the service bulletin. 

(i) If any crack is found in the structure 

during the related investigative action 

required by paragraph (h) of this AD, before 

further flight, repair in accordance with 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate; or 

the DAC (or its delegated agent). 

Credit for Previous Revisions of Service 

Bulletin 

(j) Except as provided by paragraphs (h)(1) 

and (i) of this AD, measurements and rework 

of the fillet radius done before the effective 

date of this AD in accordance with 

EMBRAER Service Bulletin 145–57–0034, 

dated October 11, 2001, are acceptable for 

compliance with the requirements of this AD. 

Alternative Methods of Compliance (AMOC) 

(k) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

has the authority to approve AMOCs for this 

AD, if requested in accordance with the 

procedures found in 14 CFR 39.19. 

Related Information 

(l) Brazilian airworthiness directive 2001–

12–03R1, effective February 4, 2002, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(m) You must use EMBRAER Service 

Bulletin 145–57–0034, Change 01, dated 

January 9, 2002, to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The service bulletin 

contains these effective pages:

Page number 

Revision 

level shown 

on page 

Date shown on 

page 

1, 2, 9, 10 ..... 01 ............. Jan. 9, 2002. 

3–8, 11–27 .... Original ..... Oct. 11, 2001. 

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 Empresa 

Brasileira de Aeronautica S.A. (EMBRAER), 

P.O. Box 343—CEP 12.225, Sao Jose dos 

Campos—SP, Brazil. 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 

18, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service

[FR Doc. 04–23925 Filed 10–28–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–SW–51–AD; Amendment 

39–13840; AD 2004–22–12] 

RIN 2120–AA64

Airworthiness Directives; MD 

Helicopters, Inc. Model 600N 

Helicopters

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

MD Helicopters, Inc. Model 600N 

helicopters that requires replacing the 

fuselage Station 75 control support 

bracket assembly (control support 

bracket), reducing the life limit, and 

revising the Limitations section of the 

applicable maintenance manual to state 

the reduced life limits on certain serialnumbered helicopters. This amendment 

is prompted by information received 

from the manufacturer indicating that 

the fatigue life of the control support 

bracket is shorter than the original 

analysis indicated. The actions specified 

by this AD are intended to prevent 

failure of the control support bracket 

and subsequent loss of control of the 

helicopter.

DATES: Effective December 3, 2004.

FOR FURTHER INFORMATION CONTACT: Fred 

Guerin, Aviation Safety Engineer, FAA, 

Los Angeles Aircraft Certification 

Office, Airframe Branch, 3960 

Paramount Blvd., Lakewood, California 

90712, telephone (562) 627–5232, fax 

(562) 627–5210.

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for the specified model 

Federal Register / Vol. 69, No. 209 / Friday, October 29, 2004 / Rules and Regulations 63055

helicopters was published in the 

Federal Register on July 29, 2004 (69 FR 

45291). That action proposed to require 

replacing the control support bracket 

assembly, part number (P/N) 369N2608–

11, on helicopters that have a yaw 

stability augmentation system (YSAS) 

installed, with an airworthy assembly, 

P/N 600N2608–1. The revised time 

limits are dependent upon the time the 

YSAS was initially installed. Also 

proposed was revising the applicable 

maintenance manual to state the 

reduced life limits. 

The FAA has reviewed MD 

Helicopters, Inc. Service Bulletin No. 

SB600N–040, dated September 18, 2003, 

which describes the revised finite life 

for the control support bracket on 

certain serial-numbered helicopters, and 

replacing them upon reaching the 

revised life limit, or no later than 

November 30, 2005, whichever occurs 

first. 

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 this AD will 

affect 13 helicopters of U.S. registry. 

Replacing the control support bracket 

will take approximately 40 work hours 

per helicopter to accomplish at an 

average labor rate of $65 per work hour. 

Required parts will cost approximately 

$5,617 per helicopter. Based on these 

figures, the total estimated cost impact 

of this AD on U.S. operators is $106,821 

to replace the control support bracket on 

each helicopter in the 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 

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 FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, 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:

2004–22–12 MD Helicopters, Inc.:

Amendment 39–13840. Docket No. 

2003–SW–51–AD.

Applicability: Model 600N helicopters, 

serial numbers with a prefix of ‘‘RN’’ and 

numbers 025, 029, 032, 034 through 038, 040, 

041, 045, 048, or 067; or, any Model 600N 

helicopter with a yaw stability augmentation 

system (YSAS) installed, and with a control 

support bracket assembly, part number (P/N) 

369N2608–11, installed, certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the fuselage Station 

75 control support bracket assembly (control 

support bracket) and subsequent loss of 

control of the helicopter, accomplish the 

following: 

(a) Replace the control support bracket, 

part number 369N2608–11, with an 

airworthy control support bracket assembly, 

P/N 600N2608–1, no later than November 30, 

2005, or by the time the helicopter reaches 

the hours time-in-service (TIS) listed in the 

chart below, whichever occurs first:

Helicopter serial number Revised finite life 

(TIS) 

RN025 ........................... 2556

RN029 ........................... 2377

RN032 ........................... 2498

RN034 ........................... 2456

RN035 ........................... 2243

RN036 ........................... 2652

RN037 ........................... 2544

RN038 ........................... 2531

RN040 ........................... 2562

RN041 ........................... 2763

RN045 ........................... 2015

RN048 ........................... 2125

RN067 ........................... 1600

Note: MD Helicopters, Inc. Service Bulletin 

No. SB600N–040, dated September 18, 2003, 

pertains to the subject of this AD.

(b) For helicopters with a YSAS installed 

that are not listed in the previous table, 

replace the control support bracket, P/N 

369N2608–11, with an airworthy control 

support bracket, P/N 600N2608–1, no later 

than November 30, 2005, or by the time the 

helicopter reaches 1,600 hours TIS since the 

installation of the YSAS. 

(c) For helicopters with no YSAS installed, 

but with a control support bracket, P/N 

369N26080–11, installed, replace the control 

support bracket, with an airworthy control 

support bracket, P/N 600N2608–1, prior to 

the installation of a YSAS. 

(d) This AD revises the Limitations section 

of the applicable maintenance manual by 

reducing the life limit of the control support 

bracket assembly, part number 369N2608–11, 

to the life limits stated in paragraph (a) of 

this AD or to 1,600 hours TIS, whichever 

occurs first. 

(e) 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 Los Angeles Aircraft 

Certification Office, Transport Airplane 

Directorate, FAA, for information about 

previously approved alternative methods of 

compliance. 

(f) This amendment becomes effective on 

December 3, 2004.

Issued in Fort Worth, Texas, on October 22, 

2004. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service.

[FR Doc. 04–24228 Filed 10–28–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 71

[Docket No. FAA–2004–18815; Airspace 

Docket No. 04–AWP–2] 

Modification of Class D and Class E 

Airspace; Prescott, AZ

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action modifies the Class 

D and Class E surface areas at Ernest A. 

Love Field (PRC) in Prescott, AZ. A 

review of airport operations and 

airspace made this action necessary. 

This action modifies the Prescott Class 

D and Class E surface areas to include 

airspace extending upward from the 

surface to and including 7,500 feet MSL 

within a 6-mile radius of Ernest A. Love 

Field.

EFFECTIVE DATE: 0901 UTC, January 20, 

2005.