Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations 57493 

Testing the Firex Electrical Circuits 

(f) Within 18 months after the 

accumulation of 15,000 total flight hours, or 

within 18 months after September 24, 2003 

(the effective date of AD 2003–17–07), 

whichever occurs later: Test the capability of 

the electrical circuits of the Firex fire 

extinguishers for the engine and the APU, as 

applicable, per the applicable alert service 

bulletin (ASB) listed in Table 1 of this AD. 

(1) For any airplane equipped with an 

APU: If any electrical circuit of the Firex fire 

extinguishers for the APU does not pass the 

testing, before further flight, accomplish the 

troubleshooting procedures specified in the 

applicable ASB. Dispatch with an inoperative 

APU is permitted for the amount of time 

specified in the Minimum Equipment List. 

Dispatch after that time is not permitted until 

the circuits are repaired per the Boeing 

Standard Wiring Practices Manual (SWPM) 

D6–82481. 

(2) For all airplanes: If any electrical circuit 

of the Firex fire extinguishers for the engine 

does not pass the testing, before further 

flight, accomplish the troubleshooting 

procedures specified in the applicable ASB, 

and repair per SWPM D6–82481. Dispatch is 

not permitted until the circuits have been 

repaired. 

Actions Accomplished Per Previous Issue of 

Service Bulletins 

(g) Tests and troubleshooting procedures 

accomplished before the effective date of this 

AD per McDonnell Douglas Alert Service 

Bulletin DC9–26A029, dated July 27, 2000; or 

MD11–26A039, dated July 31, 2000; are 

considered acceptable for compliance with 

the corresponding action specified in 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(h) An alternative method of compliance or 

adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Los 

Angeles Aircraft Certification Office (ACO), 

FAA. Operators shall submit their requests 

through an appropriate FAA Principal 

Maintenance Inspector, who may add 

comments and then send it to the Manager, 

Los Angeles ACO. 

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Los Angeles ACO. 

Special Flight Permits 

(i) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Material Incorporated by Reference 

(j) You must use the service bulletins listed 

in Table 2 of this AD to perform the actions 

that are required by this AD, unless the AD 

specifies otherwise. 

TABLE 2.—APPLICABLE SERVICE BULLETINS

Service bulletin Revision level Date 

Boeing Alert Service Bulletin DC8–26A042, including Appendix A .................................................. Original .................. January 31, 2002. 

McDonnell Douglas Alert Service Bulletin DC9–26A029 .................................................................. Revision 01 ............ May 8, 2001. 

McDonnell Douglas Alert Service Bulletin DC10–26A050 ................................................................ Original .................. July 31, 2000. 

McDonnell Douglas Alert Service Bulletin MD11–26A039 ............................................................... Revision 01 ............ November 21, 2002. 

McDonnell Douglas Alert Service Bulletin MD90–26A005 ............................................................... Original .................. July 31, 2000. 

(1) On September 24, 2003 (68 FR 50058, 

August 20, 2003), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing and McDonnell Douglas 

service bulletins listed in Table 2. 

(2) Contact Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1–L5A (D800–0024), 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 

September 20, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19438 Filed 9–30–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22485; Directorate 

Identifier 2001–NM–337–AD; Amendment 

39–14293; AD 2005–19–28] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–301, –321, –322, –341, and –342 

Airplanes; and Model A340–200 and 

A340–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–301, –321, –322, 

–341, and –342 airplanes; and Model 

A340–200 and A340–300 series 

airplanes. This AD requires repetitive 

inspections for cracks in the aft face of 

the rear spar at the area adjacent to the 

bolt holes and the end of the build slot, 

and repair if necessary. The AD also 

provides an optional terminating action 

for the repetitive inspections. This AD 

results from a report that, during fatigue 

tests of the wing, cracks were found in 

the vertical web of the rear spar between 

ribs 1 and 2 having initiated at the build 

slot. We are issuing this AD to detect 

and correct fatigue cracking in the 

vertical web of the wing rear spar, 

which could result in reduced structural 

integrity of the wing. 

DATES: Effective October 18, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 18, 2005. 

We must receive comments on this 

AD by December 2, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

57494 Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations 

for service information identified in this 

AD. 

You may examine the contents of 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., Room PL–401, Washington, DC. 

This docket number is FAA–2005–

22485; the directorate identifier for this 

docket is 2001–NM–337–AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, ANM–

116, International Branch, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Although this is a final rule that was 

not preceded by notice and an 

opportunity for public comment, we 

invite you to submit any relevant 

written data, views, or arguments 

regarding this AD. Include ‘‘Docket No. 

FAA–2005–22485; Directorate Identifier 

2001–NM–337–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may 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. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Discussion 

The Direction Generale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on certain Airbus Model A330–

301, –321, –322, –341, and –342 

airplanes; and Model A340–200 and 

A340–300 series airplanes. The DGAC 

advises that, during fatigue tests of the 

wing, cracks were found in the vertical 

web of the rear spar between ribs 1 and 

2. These fatigue cracks propagated from 

the build slot to the nearest adjacent 

bolt hole. This condition, if not 

corrected, could result in reduced 

structural integrity of the wing. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A330–57–3059, Revision 01, dated 

September 13, 2001 (for Model A330–

301, –321, –322, –341, and –342 

airplanes); and Service Bulletin A340–

57–4066, Revision 01, dated September 

13, 2001 (for Model A340–200 and 

A340–300 series airplanes). The service 

bulletins describe procedures for doing 

repetitive high-frequency eddy current 

(HFEC) inspections for cracks in the aft 

face of the rear spar at the area adjacent 

to the bolt holes and the end of the build 

slot. If no cracks are found, the service 

bulletins give intervals for repeating the 

HFEC inspection until the terminating 

action, described below, is 

accomplished. If any crack is found the 

service bulletins give the following 

procedures for repair, depending on the 

extent of the crack. 

• For any crack that has not reached 

the fastener holes ‘‘B,’’ and is still 

within a specified modification cut-out 

area, the service bulletins state that the 

airplane may continue operation at 

various reduced inspection intervals, 

depending on the length of the crack, 

until the terminating action is 

accomplished. 

• For any crack that extends to 

fastener holes ‘‘B,’’ but not beyond, the 

service bulletin gives procedures for 

doing a temporary repair and then doing 

the terminating action, described below, 

at a specified interval following the 

temporary repair. The temporary repair 

includes the related investigative action 

of a leak test after the access panels are 

installed at the work area. 

• If any crack is found that extends 

beyond the specified modification cutout area, the service bulletin specifies 

that operators should contact Airbus for 

repair instructions. 

Airbus has also issued Service 

Bulletin A330–57–3058, dated August 

29, 2001 (for Model A330–301, –321, 

–322, –341, and –342 airplanes); and 

Service Bulletin A340–57–4065, dated 

August 29, 2001 (for Model A340–200 

and A340–300 series airplanes). These 

service bulletins describe procedures for 

changing the profile of the end radius of 

the build slot to reduce the stress 

concentration in the area, which 

reduces the probability of fatigue 

cracking. The re-profiling involves first 

doing an HFEC inspection for cracks of 

the aft face of the rear spar at the area 

adjacent to the bolt holes. If cracks are 

found that will be removed by the reprofiling cut-out, the service bulletins 

specify that the re-profiling can proceed. 

If any crack is found that is outside the 

re-profiling cut-out, the service bulletins 

specify contacting Airbus for repair 

instructions before further flight. Doing 

this re-profiling eliminates the need for 

the repetitive inspection requirements 

of Airbus Service Bulletins A330–57–

3059 and A340–57–4066. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The DGAC mandated the 

service information and issued French 

airworthiness directives 2001–268(B) 

R1, dated July 25, 2001, and 2001–

269(B), dated June 27, 2001, to ensure 

the continued airworthiness of these 

airplanes in France. 

FAA’s Determination and Requirements 

of This AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DGAC has 

kept the FAA informed of the situation 

described above. We have examined the 

DGAC’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

detect and correct fatigue cracking in 

the vertical web of the wing rear spar, 

which could result in reduced structural 

integrity of the wing. This AD requires 

accomplishing the actions specified in 

the service information described 

previously. 

Differences Between the AD and the 

French Airworthiness Directives 

The applicability of the French 

airworthiness directives excludes 

airplanes on which Airbus Service 

Bulletins A330–57–3058 or A340–57–

4065 was accomplished in service, as 

applicable. However, we have not 

Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations 57495 

excluded those airplanes in the 

applicability of this AD; rather, this AD 

includes a requirement to accomplish 

the actions specified in the applicable 

service bulletin. This requirement 

would ensure that the actions specified 

in the service bulletin and required by 

this AD are accomplished on all affected 

airplanes. Operators must continue to 

operate the airplane in the configuration 

required by this AD unless an 

alternative method of compliance is 

approved. 

Unlike the procedures described in 

the service bulletins that are mandated 

by the French airworthiness directives, 

this AD would not permit further flight 

if any crack is detected. For cracks that 

have not reached fastener holes ‘‘B’’ or 

that extend to fastener holes ‘‘B,’’ but 

not beyond, this AD requires doing the 

temporary repair in accordance with the 

service bulletin. In addition, unlike the 

procedures described in the service 

bulletins, this AD would not permit 

further flight if any crack has extended 

beyond the fastener holes ‘‘B,’’ and is 

still within a specified modification cutout area. We have determined that, 

because of the safety implications and 

consequences associated with that 

cracking, any crack of this size must be 

permanently repaired (by using the reprofiling procedure) before further 

flight. 

The service bulletins that are 

mandated by the French airworthiness 

directives specify that you may contact 

the manufacturer for instructions on 

how to repair certain conditions, but 

this AD would require you to repair 

those conditions using a method that we 

or the DGAC (or its delegated agent) 

approve. In light of the type of repair 

that would be required to address the 

unsafe condition, and consistent with 

existing bilateral airworthiness 

agreements, we have determined that, 

for this AD, a repair we or the DGAC 

approve would be acceptable for 

compliance with this AD. 

These differences have been 

coordinated with the DGAC. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

The following table provides the 

estimated costs to comply with this AD 

for any affected airplane that might be 

imported and placed on the U.S. 

Register in the future. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts cost Cost per airplane 

HFEC Inspection, per inspection cycle .................... 2 $65 None ........... $130, per inspection cycle. 

Re-profiling (Optional Terminating Action) ............... 70 $65 None ........... $4,550. 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

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 the regulation: 

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. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–19–28 Airbus: Amendment 39–14293. 

Docket No. FAA–2005–22485; 

Directorate Identifier 2001–NM–337–AD. 

Effective Date 

(a) This AD becomes effective October 18, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330–

301, –321, –322, –341, and –342 airplanes; 

and Model A340–211, –212, –213, –311, 

–312, and –313 airplanes; certificated in any 

category; except airplanes on which Airbus 

Modification 41300 or 42547 has been 

accomplished, as applicable. 

57496 Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations 

Unsafe Condition 

(d) This AD results from a report that, 

during fatigue tests of the wing, cracks were 

found in the vertical web of the rear spar 

between ribs 1 and 2 having initiated at the 

build slot. The FAA is issuing this AD to 

detect and correct fatigue cracking in the 

vertical web of the wing rear spar, which 

could result in reduced structural integrity of 

the 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. 

Service Bulletin Reference 

(f) Unless otherwise specified in this AD, 

the term ‘‘service bulletin,’’ as used in this 

AD, means the Accomplishment Instructions 

of the following service bulletins, as 

applicable: 

(1) For Model A330–301, –321, –322, –341, 

and –342 airplanes: Airbus Service Bulletin 

A330–57–3059, Revision 01, dated 

September 13, 2001; and 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–57–4066, Revision 01, dated 

September 13, 2001. 

Repetitive Inspections 

(g) At the applicable threshold in Table 1 

of this AD, do a high frequency eddy current 

inspection for cracks in the aft face of the rear 

spar at the area adjacent to the bolt holes and 

the end of the build slot; and repeat the 

inspection thereafter at the applicable 

repetitive interval in Table 1 of this AD, until 

the repair required by paragraph (k) of this 

AD is accomplished. Do all inspections in 

accordance with the applicable service 

bulletin. 

TABLE 1.—INSPECTION THRESHOLDS AND INTERVALS

Model—

Threshold Repetitive interval 

The later of— The earlier of—

A330–301, –321, –322, –341, and –342 airplanes.• Before the accumulation of 10,300 total 

flight cycles or 32,000 total flight hours, 

whichever occurs earlier; or 

• 8,300 flight cycles; and 

• 25,800 flight hours. 

• Within 6 months after the effective date of 

this AD. 

A340–211, –212, –213, –311, –312, and –313 

airplanes.

• Before the accumulation of 9,800 total flight 

cycles or total 48,200 flight hours, whichever occurs earlier; or 

• 8,200 flight cycles; and 

• 40,100 flight hours. 

• Within 6 months after the effective date of 

this AD. 

Repair 

(h) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, and the crack has not reached the 

fastener holes ‘‘B’’ or extends to fastener 

holes ‘‘B,’’ but not beyond, before further 

flight: Do the temporary repair in accordance 

with the applicable service bulletin and 

repeat the inspection thereafter at the 

applicable interval in paragraph (g) of this 

AD until the permanent repair required by 

paragraph (k) of this AD is accomplished. 

(i) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, and the crack has extended beyond 

fastener holes ‘‘B,’’: Before further flight, do 

the permanent repair in paragraph (k) of this 

AD. 

(j) Where the service bulletin specifies that 

operators may contact the manufacturer for 

instructions on how to repair cracks that 

extend beyond the modification cut-out area: 

Before further flight, repair according to a 

method approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent). 

Optional Terminating Action—Permanent 

Repair (Re-Profiling) 

(k) Doing the permanent repair in 

accordance with the applicable service 

bulletin in paragraph (k)(1) or (k)(2) of this 

AD terminates the repetitive inspection 

requirements of this AD. Where the service 

bulletins in paragraph (k)(1) and (k)(2) of this 

AD specify that operators may contact the 

manufacturer for instructions on how to 

repair certain conditions: Before further 

flight, repair according to a method approved 

by either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the DGAC (or its delegated 

agent). 

(1) For Model A330–301, –321, –322, –341, 

and –342 airplanes: Airbus Service Bulletin 

A330–57–3058, dated August 29, 2001. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–57–4065, dated August 29, 

2001. 

Actions Done in Accordance With Previous 

Issues of Service Bulletins 

(l) Actions done before the effective date of 

this AD in accordance with the service 

bulletins identified in Table 2 of this AD, are 

acceptable for compliance with the 

corresponding action required by this AD. 

TABLE 2.—PREVIOUS ISSUES OF

SERVICE BULLETINS

Airbus Service Bulletins Date 

A330–57–3059 ................. March 16, 2001. 

A340–57–4066 ................. March 16, 2001. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 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 

(n) French airworthiness directives 2001–

268(B) R1, dated July 25, 2001, and 2001–

269(B), dated June 27, 2001, also address the 

subject of this AD. 

Material Incorporated by Reference 

(o) You must use the Airbus service 

bulletins identified in Table 3 of this AD to 

perform the actions that are required by this 

AD, as applicable, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of these documents in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 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. 

Federal Register / Vol. 70, No. 190 / Monday, October 3, 2005 / Rules and Regulations 57497 

TABLE 3.—MATERIAL INCORPORATED BY REFERENCE

Airbus Service Bulletins Revision level Date 

A330–57–3058 .................................................................................................................................. Original .................. August 29, 2001. 

A330–57–3059 .................................................................................................................................. 01 ........................... September 13, 2001. 

A340–57–4065 .................................................................................................................................. Original .................. August 29, 2001. 

A340–57–4066 .................................................................................................................................. 01 ........................... September 13, 2001. 

Issued in Renton, Washington, on 

September 15, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19045 Filed 9–30–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2005–22006; Airspace 

Docket No. 05–ACE–30] 

Modification of Class E Airspace; 

Sheldon Municipal Airport, IA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Direct final rule; request for 

comments. 

SUMMARY: This action modifies the size 

of the Class E5 airspace area beginning 

at 700 feet above the surface at Sheldon, 

IA to contain Instrument Flight Rule 

(IFR) operations in controlled airspace. 

The radius of the airspace area is 

expanded from within a 6.4-mile radius 

to within a 6.9-mile radius of the 

airport. This action brings the Class E5 

airspace area into compliance with FAA 

directives. 

DATES: This direct final rule is effective 

on 0901 UTC, December 22, 2005. 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 28, 2005. 

ADDRESSES: Send comments on this 

proposal to the Docket Management 

System, U.S. Department of 

Transportation, Room Plaza 401, 400 

Seventh Street, SW., Washington, DC 

20590–0001. You must identify the 

docket number FAA–2005–22006/ 

Airspace Docket No. 05–ACE–30, at the 

beginning of your comments. You may 

also submit comments on the Internet at 

http://dms.dot.gov. You may review the 

public docket containing the proposal, 

any comments received, and any final 

disposition in person in the Dockets 

Office between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

1–800–647–5527) is on the plaza level 

of the Department of Transportation 

NASSIF Building at the above address. 

FOR FURTHER INFORMATION CONTACT: 

Brenda Mumper, Air Traffic Division, 

Airspace Branch, ACE–520A, DOT 

Regional Headquarters Building, Federal 

Aviation Administration, 901 Locust, 

Kansas City, MO 64106; telephone: 

(816) 329–2524. 

SUPPLEMENTARY INFORMATION: This 

amendment to 14 CFR 71 modifies the 

Class E airspace beginning at 700 feet 

above the surface at Sheldon Municipal 

Airport, IA to contain Instrument Flight 

Rule (IFR) operations in controlled 

airspace. The area will be depicted on 

appropriate aeronautical charts. Class E 

airspace areas are published in 

Paragraph 6005 of FAA Order 7400.9N, 

Airspace Designations and Reporting 

Points, dated September 1, 2005, and 

effective September 16, 2005, which is 

incorporated by reference in 14 CFR 

71.1. The Class E airspace designations 

listed in this document will be 

published subsequently in the Order. 

The Direct Final Rule Procedure 

The FAA anticipates that this 

regulation will not result in adverse or 

negative comment and, therefore, is 

issuing it as a direct final rule. Previous 

actions of this nature have not been 

controversial and have not resulted in 

adverse comments or objections. Unless 

a written adverse or negative comment, 

or a written notice of intent to submit 

an adverse or negative comment is 

received within the comment period, 

the regulation will become effective on 

the date specified above. After the close 

of the comment period, the FAA will 

publish a document in the Federal 

Register indicating that no adverse or 

negative comments were received and 

confirming the date on which the final 

rule will become effective. If the FAA 

does receive, within the comment 

period, an adverse or negative comment, 

or written notice of intent to submit 

such a comment, a document 

withdrawing the direct final rule will be 

published in the Federal Register, and 

a notice of proposed rulemaking may be 

published with a new comment period. 

Comments Invited 

Interested parties are invited to 

participate in this rulemaking by 

submitting such written data, views, or 

arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers and be submitted in 

triplicate to the address listed above. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

on this notice must submit with those 

comments a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2005–22006/Airspace 

Docket No. 05–ACE–30.’’ The postcard 

will be date/time stamped and returned 

to the commenter. 

Agency Findings 

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. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation—(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) 

does not warrant preparation of a 

Regulatory Evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified that this rule, when 

promulgated, will not have a significant 

economic impact on a substantial 

number of small entities under the 

criteria of the Regulatory Flexibility Act. 

This rulemaking is promulgated 

under the authority described in