72368 Federal Register / Vol. 70, No. 232 / Monday, December 5, 2005 / Rules and Regulations 

Page No. 

Revision 

level 

shown on 

page 

Date shown on 

page 

1, 3 ............. 02 ........... March 18, 2005. 

2, 17, 18 ..... 01 ........... Nov. 9, 2004. 

4–16, 19–21 Original .. April 6, 2004. 

The Director of the Federal Register 

approved the incorporation by reference of 

this document in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Empresa 

Brasileira de Aeronautica S.A. (EMBRAER), 

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

Campos—SP, Brazil, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the 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 

November 25, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–23555 Filed 12–2–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22454; Directorate 

Identifier 2001–NM–108–AD; Amendment 

39–14395; AD 2005–25–02] 

RIN 2120–AA64 

Airworthiness Directives; Aerospatiale 

Model ATR42–200, ATR42–300, and 

ATR42–320 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Aerospatiale Model 

ATR42–200, ATR42–300, and ATR42–

320 airplanes. That AD currently 

requires inspections to determine the 

proper installation of rivets in certain 

key holes and to detect cracks in the 

area of the key holes where rivets are 

missing; and correction of 

discrepancies. The existing AD also 

requires various inspections of the 

subject area for discrepancies, and 

corrective actions if necessary; and 

replacement of certain cargo door hinges 

with new hinges. For certain airplanes, 

the existing AD also requires 

replacement of friction plates, stop 

fittings, and bolts with new parts. This 

new AD requires additional corrective 

actions for certain airplanes. This AD 

results from discovery of cracks around 

key holes on certain fuselage frames 

where rivets were missing. We are 

issuing this AD to prevent fatigue cracks 

of the cargo door skin, certain frames, 

and entry door stop fittings and friction 

plates, which could result in reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

January 9, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 9, 2006. 

On April 26, 2000 (65 FR 15226, 

March 22, 2000), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications. 

On November 18, 1993 (58 FR 53853, 

October 19, 1993), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

publication. 

ADDRESSES: You may examine the 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., Nassif Building, room PL–401, 

Washington, DC. 

Contact Aerospatiale, 316 Route de 

Bayonne, 31060 Toulouse, Cedex 03, 

France, for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–1137; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (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 street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2000–05–26, amendment 

39–11636 (65 FR 15226, March 22, 

2000). The existing AD applies to all 

ATR42–200, ATR42–300 and ATR42–

320 airplanes. That NPRM was 

published in the Federal Register on 

September 19, 2005 (70 FR 54856). That 

NPRM proposed to continue to require 

inspections to determine the proper 

installation of rivets in certain key holes 

and to detect cracks in the area of the 

key holes where rivets are missing; and 

correction of discrepancies. That NPRM 

also proposed to continue to require 

various inspections of the subject area 

for discrepancies, and corrective actions 

if necessary; and replacement of certain 

cargo door hinges with new hinges. For 

certain airplanes, that NPRM proposed 

to continue to require replacement of 

friction plates, stop fittings, and bolts 

with new parts. That NPRM further 

proposed to require additional 

corrective actions for certain airplanes. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Clarification of Effective Date 

We have revised Note 2 of this AD to 

include the effective date of AD 2000–

05–26. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the changes 

described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

This AD will affect about 106 

Aerospatiale Model ATR42–200, 

ATR42–300, and ATR42–320 airplanes 

of U.S. registry. 

The general visual inspection of 

fuselage frames 25 and 27 that is 

required by AD 2000–05–26 and 

Federal Register / Vol. 70, No. 232 / Monday, December 5, 2005 / Rules and Regulations 72369 

retained in this AD takes about 3 work 

hours per airplane, at an average labor 

rate of $65 per work hour. Based on 

these figures, the estimated cost of that 

currently required action is $195 per 

airplane. 

The cargo door hinge and skin 

replacement that is required by AD 

2000–05–26 and retained in this AD 

takes about 250 work hours per 

airplane, at an average labor rate of $65 

per work hour. Required parts will cost 

approximately $9,880 per airplane. 

Based on these figures, the estimated 

cost of the currently required action is 

$26,130 per airplane. 

The general visual inspection of the 

key and tooling holes that is required by 

AD 2000–05–26 takes about 100 work 

hours per airplane, at an average rate of 

$65 per work hour. Based on these 

figures, the estimated cost of that 

currently required action is $6,500 per 

airplane. 

The eddy current and detailed visual 

inspections of the forward entry door 

stop fitting and friction plate that are 

required by AD 2000–05–26 take about 

2 work hours per airplane, at an average 

rate of $65 per work hour. Based on 

these figures, the estimated cost of those 

currently required actions is $130 per 

airplane. 

The replacement of the forward entry 

door stop fitting, friction plate, and 

upper door corner that is required by 

AD 2000–05–26 takes about 50 work 

hours per airplane, at an average rate of 

$65 per work hour. The manufacturer 

has committed previously to its 

customers that it will bear the cost of 

replacement parts. As a result, the cost 

of those parts is not attributable to this 

AD. Based on these figures, the 

estimated cost of that currently required 

action is $3,250 per airplane. 

The new actions required by this AD 

will take about 250 work hours per 

airplane, at an average labor rate of $65 

per work hour. Required parts will cost 

about $9,880 per airplane. Based on 

these figures, the estimated cost of the 

new actions required by this AD is 

$26,130 per airplane. 

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 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 and placed it in the AD docket. 

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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing amendment 39–11636 (65 FR 

15226, March 22, 2000) and adding the 

following new airworthiness directive 

(AD): 

2005–25–02 Aerospatiale: Amendment 39–

14395. Docket No. FAA–2005–22454; 

Directorate Identifier 2001–NM–108–AD. 

Effective Date 

(a) This AD becomes effective January 9, 

2006. 

Affected ADs 

(b) This AD supersedes AD 2000–05–26. 

Applicability 

(c) This AD applies to all Aerospatiale 

Model ATR42–200, ATR42–300, and ATR–

320 airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from discovery of 

cracks around key holes on certain fuselage 

frames where rivets were missing. We are 

issuing this AD to prevent fatigue cracks of 

the cargo door skin, certain frames, and entry 

door stop fittings and friction plates, which 

could result in reduced structural integrity of 

the airplane. 

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. 

Restatement of the Requirements of AD 

2000–05–26 

Frame 25 and 27 Inspection 

(f) For airplanes having serial numbers 005 

through 016 inclusive, 018 through 030 

inclusive, 032 through 036 inclusive, 038, 

040, 042, 043, 048 through 062 inclusive, 064 

through 090 inclusive, 092 through 094 

inclusive, and 096 through 228 inclusive: 

Prior to the accumulation of 36,000 total 

flight cycles, or within 180 days after April 

26, 2000, (the effective date of AD 2000–05–

26) whichever occurs later, conduct a general 

visual inspection of fuselage frames 25 and 

27 to verify the proper installation of a rivet 

in each of the key holes, in accordance with 

Avions de Transport Regionale (ATR) Service 

Bulletin ATR42–53–0070, Revision 2, dated 

March 22, 1993; or Revision 3, dated 

February 19, 1999. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Note 2: Inspection of fuselage frames 25 

and 27 accomplished prior to April 26, 2000, 

in accordance with ATR Service Bulletin 

ATR42–53–0070, dated June 10, 1991; or 

Revision 1, dated June 12, 1992; is 

considered acceptable for compliance with 

the requirements of paragraph (f) of this AD. 

(1) If a rivet is installed in each of the key 

holes, no further action is required by this 

paragraph. 

(2) If a rivet is not installed in each of the 

key holes, prior to further flight, perform an 

eddy current inspection of each open key 

hole to detect cracks, in accordance with the 

service bulletin. 

72370 Federal Register / Vol. 70, No. 232 / Monday, December 5, 2005 / Rules and Regulations 

(i) If no crack is found during the eddy 

current inspection, prior to further flight, 

install a rivet in the open key hole in 

accordance with the service bulletin. After 

such installation, no further action is 

required by this paragraph for that key hole. 

(ii) If any crack is found during the eddy 

current inspection, prior to further flight, 

repair the crack in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the Direction Ge ́ne ́rale 

de l’Aviation Civile (DGAC) (or its delegated 

agent). For a repair method to be approved 

by the Manager, International Branch, ANM–

116, as required by this paragraph, the 

Manager’s approval letter must specifically 

reference this AD. 

Inspection and Modification of Cargo Door 

Structure 

(g) For airplanes equipped with a cargo 

compartment door on which Aerospatiale 

Modification 3191 has not been 

accomplished: Prior to the accumulation of 

27,000 total flight cycles, or within 180 days 

after April 26, 2000, whichever occurs later, 

except as provided by paragraph (h) of this 

AD, replace the hinges on the cargo 

compartment door and fuselage (including 

inspections for fastener type and tolerances, 

hole diameters, or cracking, and repair; as 

applicable) with new improved hinges, in 

accordance with paragraph 2. of the 

Accomplishment Instructions of ATR Service 

Bulletin ATR42–52–0058, Revision 1, dated 

March 1, 1995; or ATR42–52–0058, Revision 

2, dated June 22, 2000. 

(h) Where the instructions in ATR Service 

Bulletin ATR42–52–0058, Revision 1, dated 

March 1, 1995; or ATR42–52–0058, Revision 

2, dated June 22, 2000, specify that ATR is 

to be contacted for a repair, prior to further 

flight, repair in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, or the DGAC (or its 

delegated agent). 

Frame Inspection 

(i) For airplanes having serial numbers 003 

through 208 inclusive: Prior to the 

accumulation of 36,000 total flight cycles, or 

within 180 days after April 26, 2000, 

whichever occurs later, conduct a general 

visual inspection of the identified fuselage 

frames for proper installation of a rivet in 

each of the tooling and key holes, in 

accordance with ATR Service Bulletin 

ATR42–53–0076, Revision 2, dated October 

15, 1996; or Revision 3, dated February 19, 

1999. 

(1) If a rivet is installed in each of the 

tooling or key holes, no further action is 

required by this paragraph. 

(2) If a rivet is not installed in each of the 

tooling and key holes, prior to further flight, 

perform a detailed inspection of each open 

tooling or key hole to detect cracks, in 

accordance with the service bulletin. 

Note 3: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(i) If no crack is found during the detailed 

inspection required by paragraph (i)(2) of this 

AD, prior to further flight, install a rivet in 

the open hole in accordance with the service 

bulletin. 

(ii) If any crack is found during the 

inspection required by paragraph (i)(2) of this 

AD, prior to further flight, repair the crack in 

accordance with a method approved by the 

Manager, International Branch, ANM–116; or 

the DGAC (or its delegated agent). 

Inspection and/or Replacement of Entry Door 

Structure 

(j) For Model ATR42–300 airplanes having 

serial numbers listed in ATR Service Bulletin 

ATR42–52–0052, Revision 1, dated March 2, 

1993: Except as provided by paragraph (f) of 

this AD, prior to the accumulation of 10,000 

total flight cycles, or within 90 days after 

April 26, 2000, whichever occurs later, 

accomplish the requirements of paragraphs 

(j)(1) and (j)(2) of this AD. 

(1) Perform an eddy current inspection of 

the forward entry door stop holes to detect 

cracking, in accordance with the service 

bulletin. If any cracking is detected, prior to 

further flight, replace any cracked forward 

entry door stop fitting with a new fitting, in 

accordance with the service bulletin. 

(2) Perform a detailed inspection of the 

forward entry door friction plates for wear, in 

accordance with the service bulletin. If wear 

is found on any friction plate, and the wear 

has a depth equal to or greater than 0.8mm 

(0.0315 in.), prior to further flight, replace the 

friction plate with a new or serviceable part 

in accordance with the service bulletin. 

(k) For Model ATR42–300 airplanes listed 

in ATR Service Bulletin ATR42–52–0052, 

Revision 1, dated March 2, 1993, 

accomplishment of the requirements of 

paragraph (l) of this AD at the time specified 

in paragraph (j) of this AD constitutes 

terminating action for the requirements of 

paragraph (j) of this AD. 

(l) For Model ATR42–300 airplanes listed 

in ATR Service Bulletin ATR42–52–0059, 

dated February 16, 1995: Prior to the 

accumulation of 18,000 total flight cycles, or 

within 180 days after April 26, 2000, 

whichever occurs later, accomplish the 

requirements of paragraphs (l)(1), (l)(2), and 

(l)(3) of this AD in accordance with the 

service bulletin. 

(1) Replace the forward entry door friction 

plates with improved friction plates. 

(2) Replace the upper corners of the 

forward entry door surround structure with 

improved door surround corners. 

(3) Replace the forward entry door stop 

fittings and bolts with improved fittings and 

bolts. 

New Requirements of This AD 

Replacing Hinges on the Cargo Compartment 

Door and Fuselage 

(m) For airplanes identified as having main 

serial numbers (MSNs) 317, 319, 321, 323, 

325, 327, 329 through 335 inclusive, 360, and 

368, that are equipped with a cargo 

compartment door on which Aerospatiale 

Modification 3191 has not been 

accomplished: Prior to the accumulation of 

27,000 total flight hours, or within 180 days 

after the effective date of this AD, whichever 

occurs later, replace the hinges on the cargo 

compartment door and fuselage (including 

inspections for fastener type and tolerances, 

hole diameters, or cracking, and repair; as 

applicable) with new improved hinges, in 

accordance with the Accomplishment 

Instructions of Avions de Transport Regional 

(ATR) Service Bulletin ATR42–52–0058, 

Revision 2, dated June 22, 2000. 

(n) Where the instructions in ATR Service 

Bulletin ATR42–52–0058, Revision 2, dated 

June 22, 2000, specify that ATR is to be 

contacted for a repair, prior to further flight, 

repair in accordance with a method approved 

by the Manager, International Branch, ANM–

116; or the DGAC (or its delegated agent). 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) 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. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(p) French airworthiness directive 2000–

337–079(B), dated July 26, 2000, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(q) You must use the service bulletins 

listed in Table 1 of this AD to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

Avions de Transport regional service bulletin Revision level Date 

ATR42–52–0052 ............................................................... 1 ......................................... March 2, 1993. 

ATR42–52–0058 ............................................................... 1 ......................................... March 1, 1995. 

ATR42–52–0058 ............................................................... 2 ......................................... June 22, 2000. 

ATR42–52–0059 ............................................................... Original ............................... February 16, 1995. 

ATR42–53–0070 ............................................................... 2 ......................................... March 22, 1993. 

Federal Register / Vol. 70, No. 232 / Monday, December 5, 2005 / Rules and Regulations 72371 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE—Continued 

Avions de Transport regional service bulletin Revision level Date 

ATR42–53–0070 ............................................................... 3 ......................................... February 19, 1999.

ATR42–53–0076 ............................................................... 2 ......................................... October 15, 1996. 

ATR42–53–0076 ............................................................... 3 ......................................... February 19, 1999.

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Avions de Transport Regional Service 

Bulletin ATR42–52–0058, Revision 2, dated 

June 22, 2000, in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On April 26, 2000 (65 FR 15226, March 

22, 2000), the Director of the Federal Register 

approved the incorporation by reference of 

the Avions de Transport Regionale service 

information as listed in Table 2 of this AD. 

TABLE 2.—PREVIOUS MATERIAL INCORPORATED BY REFERENCE

Avions de Transport regionale service bulletin Revision level Date 

ATR42–52–0052 ............................................................... 1 ......................................... March 2, 1993. 

ATR42–52–0058 ............................................................... 1 ......................................... March 1, 1995. 

ATR42–52–0059 ............................................................... Original ............................... February 16, 1995. 

ATR42–53–0070 ............................................................... 3 ......................................... February 19, 1999.

ATR42–53–0076 ............................................................... 2 ......................................... October 15, 1996. 

ATR42–53–0076 ............................................................... 3 ......................................... February 19, 1999.

(3) On November 18, 1993, (58 FR 53853, 

October 19, 1993), the Director of the Federal 

Register approved the incorporation by 

reference of Avions de Transport Regionale 

Service Bulletin ATR42–53–0070, Revision 2, 

dated March 22, 1993. 

(4) Contact Aerospatiale, 316 Route de 

Bayonne, 31060 Toulouse, Cedex 03, France, 

for copy of this service information. You may 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the 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 

November 25, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–23556 Filed 12–2–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2005–21256; Airspace 

Docket No. 05–AGL–04] 

Establishment of Class D Airspace; 

Eau Claire, WI 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Direct final rule; confirmation of 

effective date. 

SUMMARY: This document confirms the 

effective date of the direct final rule 

which establishes Class D airspace at 

Eau Claire, WI. 

EFFECTIVE DATE: 0901 UTC, October 27, 

2005. 

FOR FURTHER INFORMATION CONTACT: 

Steve Davis, FAA Terminal Operations, 

Central Service Office, Airspace and 

Procedures Branch, AGL–530, Federal 

Aviation Administration, 2300 East 

Devon Avenue, Des Plaines, Illinois 

60018, telephone (847) 294–7131, or 

David Sapadin (847) 294–7477. 

SUPPLEMENTARY INFORMATION: The FAA 

published this direct final rule with a 

request for comments in the Federal 

Register on September 6, 2005 (70 FR 

52903). The FAA uses the direct final 

rulemaking procedure for a noncontroversial rule where the FAA 

believes that there will be no adverse 

public comment. This direct final rule 

advised the public that no adverse 

comments were anticipated, and that 

unless a written adverse comment, or a 

written notice of intent to submit such 

an adverse comment, were received 

within the comment period, the 

regulation would become effective on 

that date. 

Issued in Des Plaines, Illinois, on 

November 1, 2005. 

Nancy B. Kort, 

Area Director, Central Terminal Operations. 

[FR Doc. 05–23633 Filed 12–2–05; 8:45 am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA 2005–20417; Airspace 

Docket No. 05–ANM–06] 

Amendment to Class E Airspace; 

Wenatchee, WA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This final rule will revise the 

Class E airspace area at Wenatchee, WA. 

Additional Class E airspace is necessary 

to accommodate aircraft using a new 

Instrument Landing System (ILS) 

Standard Instrument Approach 

Procedure (SIAP) at Wenatchee/ 

Pangborn Memorial Memorial Airport. 

This change is necessary for the safety 

of Instrument Flight Rules (IFR) aircraft 

executing the new SIAP at Wenatchee/ 

Pangborn Memorial Airport, Wenatchee, 

WA. 

EFFECTIVE DATE: 0901 UTC, January 19, 

2006. 

FOR FURTHER INFORMATION CONTACT: Ed 

Haeseker, Federal Aviation 

Administration, Western En Route and 

Oceanic Area Office, Airspace Branch, 

1601 Lind Avenue, SW., Renton, WA 

98055–4056; telephone (425) 227–2527. 

SUPPLEMENTARY INFORMATION: 

History 

On May 25, 2005, the FAA proposed 

to amend Title 14 Code of Federal 

Regulations part 71 (CFR part 71) by 

revising Class E airspace at Wenatchee, 

WA (70 FR 20093). The proposed action