69288 Federal Register / Vol. 70, No. 219 / Tuesday, November 15, 2005 / Proposed Rules 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed 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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

BAE Systems (Operations) Limited 

(Formerly British Aerospace Regional 

Aircraft): Docket No. FAA–2005–22974; 

Directorate Identifier 2005–NM–180–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by December 15, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to BAE Systems 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A series airplanes, 

certificated in any category, on which 

Modification HCM00301A or B has been 

done, and on which Modification 

HCM0169A has not been done. 

Unsafe Condition 

(d) This AD results from a report of chafing 

along the seal/fuselage contact area under the 

wing-to-fuselage fairing access panels on 

both sides of the fuselage. We are issuing this 

AD to ensure the structural integrity of the 

fuselage. 

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) Before the airplane accumulates 1,000 

total flight cycles, or within 500 flight cycles 

after the effective date of this AD, whichever 

occurs later: Inspect, using a dial test 

indicator, to measure the depth of any 

chafing or scoring in the skin along the full 

length of the fairing from forward to aft ends 

at the point of contact between the seal and 

fuselage on both sides of the fuselage. Do 

applicable related investigative/corrective 

actions in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletins ISB.53–005, Revision 2, dated 

February 16, 2004, and ISB.53–067, Revision 

3, dated June 27, 2005, except as required by 

paragraph (g) of this AD. Do related 

investigative/corrective actions and repeat 

the inspection to measure the chafing/scoring 

at the times specified in the service bulletins, 

as applicable. 

Exceptions to Service Bulletin Specifications 

(g) Where the service bulletins referenced 

in this AD specify to contact the 

manufacturer for repair instructions: Before 

further flight, repair using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the Civil 

Aviation Authority (or its delegated agent). 

(h) Although the service bulletins 

referenced in this AD specify to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Credit for Earlier Accomplishment 

(i) Inspections and applicable investigative 

and corrective actions done before the 

effective date of this AD are acceptable for 

compliance with the requirements of 

paragraph (f) of this AD if done in accordance 

with one of the service bulletin versions 

identified in Table 1 of this AD, as 

applicable. 

TABLE 1.—CREDIT SERVICE BULLETINS

BAE Systems (Operations) limited service bulletin Revision level Date 

ISB.53–005 ....................................................................... Original ............................................................................. August 15, 1984. 

Revision 1 ........................................................................ April 19, 1984. 

ISB.53–067 ....................................................................... Original ............................................................................. December 23, 1987. 

Revision 1 ........................................................................ February 16, 1990. 

Revision 2 ........................................................................ February 16, 2004. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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 

(k) British airworthiness directive G–2005–

0020, dated July 6, 2005, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on 

November 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22587 Filed 11–14–05; 8:45 am] 

BILLING CODE 4910–13–U 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22973; Directorate 

Identifier 2004–NM–67–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A330–300, A340–200, and 

A340–300 Series Airplanes; and A340–

541 and A340–642 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Airbus Model A330–200, A330–300, 

Federal Register / Vol. 70, No. 219 / Tuesday, November 15, 2005 / Proposed Rules 69289 

A340–200, and A340–300 series 

airplanes; and A340–541 and A340–642 

airplanes. This proposed AD would 

require operators to revise the 

Airworthiness Limitations section of the 

Instructions for Continued 

Airworthiness to incorporate new 

information. This information includes, 

for all affected airplanes, decreased life 

limit values for certain components; and 

for Model A330–200 and –300 series 

airplanes, new inspections, compliance 

times, and new repetitive intervals to 

detect fatigue cracking, accidental 

damage, or corrosion in certain 

structures. This proposed AD results 

from a revision to subsection 9–1 of the 

Airbus A330 and A340 Maintenance 

Planning Documents (MPD) for Life 

Limits/Monitored parts, and subsection 

9–2 of the Airbus A330 MPD for 

Airworthiness Limitations Items. We are 

proposing this AD to ensure the 

continued structural integrity of these 

airplanes. 

DATES: We must receive comments on 

this proposed AD by December 15, 

2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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. 

• By 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, 

for service information identified in this 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer 

International Branch, ANM–116, FAA, 

International Branch, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 

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

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22973; Directorate Identifier 

2004–NM–67–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments submitted by the 

closing date and may amend the 

proposed 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 proposed AD. 

Using the search function of our docket 

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 can 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you can visit http:// 

dms.dot.gov. 

Examining the Docket 

You can examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on all Airbus Model A330–200, 

A330–300, A340–200, and A340–300 

series airplanes; and A340–541 and 

A340–642 airplanes. 

The DGAC advises that Airbus A300 

Maintenance Planning Document (MPD) 

subsection 9–2, ‘‘Airworthiness 

Limitations Items,’’ has been revised to 

reference Issue 12, dated November 1, 

2003, of the Airworthiness Limitations 

section (ALS) of the Instructions for 

Continued Airworthiness. Issue 12 

results from the completion of fatigue 

and damage tolerance evaluations and 

introduces, for Model A330 series 

airplanes, new inspections, compliance 

times, and repetitive intervals to detect 

fatigue cracking, accidental damage, or 

corrosion in certain structures of the 

airplane. 

The DGAC also advises that the list of 

life limited/monitored parts given in 

Section 9–1 of the Airbus A330 and 

A340 MPDs has been revised. The 

revision provides mandatory 

replacement times approved under 

section 25.571 of the Joint Aviation 

Requirements and the Federal Aviation 

Regulations (14 CFR 25.571), and 

applies to all Airbus Model A330–200, 

A330–300, A340–200, and A340–300 

series airplanes; and A340–541 and 

A340–642 airplanes. The DGAC advises 

that certain life limits must be imposed 

for various components on these 

airplanes to prevent the onset of fatigue 

cracking, and that the limits for certain 

components have decreased in these 

new revisions. 

Incorporating these revisions into the 

Airworthiness Limitations section of the 

Instructions for Continued 

Airworthiness is intended to ensure the 

continued structural integrity of these 

airplanes. 

Relevant Service Information 

Airbus has issued Document AI/SE–

M4/95A.0089/97, ‘‘A330 Airworthiness 

Limitation Items’’ (ALI), Issue 12, dated 

November 1, 2003, of the Airbus A330 

MPD, Section 9–2. The ALI document 

contains items related to evaluations of 

fatigue and damage tolerance arising 

from fatigue-critical and flight-cycle 

accidental damage, and a requirement to 

control corrosion. Issue 12 specifies new 

inspections, compliance times, and 

repetitive intervals to detect fatigue 

cracking, accidental damage, or 

corrosion in certain structures. 

Airbus has also issued Section 9–1, 

‘‘Life Limits/Monitored Parts,’’ Revision 

05, dated April 7, 2005, of the Airbus 

A330 and A340 MPDs. The MPDs 

include the airworthiness limits for 

Airbus Model A330–200, A330–300, 

A340–200, and A340–300 series 

airplanes; and A340–541 and A340–642 

airplanes. Revision 05 increases the life 

limits of certain components of the MLG 

and nose landing gear (NLG) for Model 

A340–541 and A340–642 airplanes, and 

decreases the existing life limits for 

other MLG and NLG components for 

other Airbus Model A330–200, A330–

300, A340–200, and A340–300 series 

airplanes. 

Accomplishing the actions specified 

in these documents is intended to 

adequately address the unsafe 

condition. The DGAC mandated these 

documents and issued French 

airworthiness directives F–2004–024, 

dated February 18, 2004; F–2005–069, 

dated April 27, 2005; and F–2005–070, 

dated April 27, 2005; to ensure the 

69290 Federal Register / Vol. 70, No. 219 / Tuesday, November 15, 2005 / Proposed Rules 

continued airworthiness of these 

airplanes in France. 

Explanation of Action Taken by the 

FAA 

In accordance with airworthiness 

standards requiring ‘‘damage tolerance 

assessments’’ for transport category 

airplanes (section 25.1529 of the Federal 

Aviation Regulations (14 CFR 25.1529), 

and the Appendices referenced in that 

section), all products certificated to 

comply with that section must have 

Instructions for Continued 

Airworthiness (or, for some products, 

maintenance manuals) that include an 

ALS. That section must set forth: 

• Mandatory replacement times for 

structural components, 

• Structural inspection intervals, and 

• Related approved structural 

inspection procedures necessary to 

show compliance with the damagetolerance requirements. 

Compliance with the terms specified 

in the ALS is required by sections 43.16 

(for persons maintaining products) and 

91.403 (for operators) of the Federal 

Aviation Regulations (14 CFR 43.16 and 

91.403). 

In order to require compliance with 

these inspection intervals and life 

limits, we must engage in rulemaking, 

namely the issuance of an AD. For 

products certificated to comply with the 

referenced part 25 requirements, it is 

within our authority to issue an AD 

requiring a revision to the ALS that 

includes reduced life limits, or new or 

different structural inspection 

requirements. These revisions then are 

mandatory for operators under section 

91.403(c) of the Federal Aviation 

Regulations (14 CFR 91.403), which 

prohibits operation of an airplane for 

which airworthiness limitations have 

been issued unless the inspection 

intervals specified in those limitations 

have been complied with. 

After that document is revised, as 

required, and the AD has been fully 

complied with, the life limit or 

structural inspection change remains 

enforceable as a part of the 

airworthiness limitations. (This is 

analogous to ADs that require changes 

to the Limitations Section of the 

Airplane Flight Manual.) 

Requiring a revision of the 

airworthiness limitations, rather than 

requiring individual inspections, is 

advantageous for operators because it 

allows them to record AD compliance 

status only once—at the time they make 

the revision—rather than after every 

inspection. It also has the advantage of 

keeping all airworthiness limitations, 

whether imposed by original 

certification or by AD, in one place 

within the operator’s maintenance 

program, thereby reducing the risk of 

non-compliance because of oversight or 

confusion. 

FAA’s Determination and Requirements 

of the Proposed 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 proposing this AD, 

which would require operators to revise 

the ALS of the Instructions for 

Continued Airworthiness to incorporate 

new inspections, compliance times, and 

repetitive intervals to detect fatigue 

cracking, accidental damage, or 

corrosion in certain structures. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work 

hours 

Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Revise the ALS ......................... 1 $65 None ......................................... $65 20 $1,300 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 proposed 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 proposed 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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Federal Register / Vol. 70, No. 219 / Tuesday, November 15, 2005 / Proposed Rules 69291 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2005–22973; 

Directorate Identifier 2004–NM–67–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

December 15, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A330–201, –202, –203, –223, and –243 

airplanes; A330–301, –321, –322, –323, –341, 

–342, –343 airplanes; A340–211, –212, and 

–213 airplanes; A340–311, –312, and –313 

airplanes; A340–541 airplanes; and A340–

642 airplanes; certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (h) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529. 

Unsafe Condition 

(d) This AD results from a revision to 

subsection 9–1 of the Airbus A330 and A340 

Maintenance Planning Documents (MPD) for 

Life Limits/Monitored parts, and subsection 

9–2 of the Airbus A330 MPD for 

Airworthiness Limitations Items. We are 

issuing this AD to ensure the continued 

structural integrity of these airplanes. 

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. 

Airworthiness Limitations Revision 

(f) Within 3 months after the effective date 

of this AD, revise the Airworthiness 

Limitations section (ALS) of the Instructions 

for Continued Airworthiness by 

incorporating into the ALS the documents in 

paragraph (f)(1) and (f)(2) of this AD, as 

applicable. 

(1) Document AI/SE–M4/95A.0089/97, 

‘‘Airworthiness Limitations Items,’’ Issue 12, 

dated November 1, 2003, Section 9–2 of the 

Airbus A330 Maintenance Planning 

Document (MPD). 

(2) Section 9–1, ‘‘Life Limits/Monitored 

parts,’’ Revision 05, dated April 7, 2005, of 

the Airbus A330 and A340 MPDs. 

(g) Except as provided by paragraph (h) of 

this AD: After the actions in paragraph (f) of 

this AD have been accomplished, no 

alternative inspections or inspection 

intervals may be approved for the structural 

elements specified in the documents listed in 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(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 

(i) French airworthiness directives F–

2004–024, dated February 18, 2004; F–2005–

069, dated April 27, 2005; and F–2005–070, 

dated April 27, 2005; also address the subject 

of this AD. 

Issued in Renton, Washington, on 

November 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22588 Filed 11–14–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22873; Directorate 

Identifier 2005–NM–197–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Bombardier Model CL–600–

2B19 (Regional Jet Series 100 & 440) 

airplanes. This proposed AD would 

require replacing the Camloc fasteners 

on the sidewall of the center pedestal. 

This proposed AD results from reports 

of the Camloc fasteners on the sidewall 

of the center pedestal disengaging and 

interfering with an inboard rudder 

pedal. We are proposing this AD to 

prevent these fasteners from disengaging 

and interfering with an inboard rudder 

pedal, which could reduce directional 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by December 15, 

2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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 Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, 

Station Centre-ville, Montreal, Quebec 

H3C 3G9, Canada, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Daniel Parrillo, Aerospace Engineer, 

Systems and Flight Test Branch, ANE–

172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 228–7305; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2005–22873; Directorate 

Identifier 2005–NM–197–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed 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 proposed AD. 

Using the search function of that Web