Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules 58623 

accordance with Boeing Alert Service 

Bulletin 767–27A0194 or 767–27A0195, both 

dated August 21, 2003, as applicable: Within 

4,000 flight hours or 24 months after the 

effective date of this AD, whichever is first, 

accomplish the inspections and perform any 

applicable corrective action before further 

flight in accordance with Work Package 3 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 767–27A0194 or Boeing 

Service Bulletin 767–27A0195, both Revision 

1, both dated July 21, 2005; as applicable. 

(h) For Model 767 airplanes that have line 

numbers 002 through 175 inclusive: 

Accomplishing the initial inspection, 

applicable corrective action, and lubrication 

before the effective date of this AD in 

accordance with Boeing Alert Service 

Bulletin 767–27A0185, dated July 10, 2003; 

is considered acceptable for compliance with 

the applicable actions required by paragraph 

(f) of this AD. 

Note 1: Boeing Service Bulletins 767–

27A0194 and 767–27A0195, both Revision 1, 

both dated July 21, 2005, refer to the 767 

Airplane Maintenance Manuals (AMM) in 

Table 1 of this AD as additional sources of 

service information for accomplishing the 

detailed inspections, lubrications, freeplay 

measurements, and corrective action. 

TABLE 1.—ADDITIONAL SOURCES OF

SERVICE INFORMATION

Boeing AMM Subject 

767–200 ................................ 27–41–10 

767–200 ................................ 12–21–05 

Parts Installation 

(i) As of the effective date of this AD, no 

person may install on any airplane a 

horizontal stabilizer trim actuator unless it is 

new or has been overhauled in accordance 

with Boeing Service Bulletins 767–27A0194 

and 767–27A0195, both Revision 1, both 

dated July 21, 2005; or has been inspected, 

lubricated, and measured in accordance with 

paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Issued in Renton, Washington, on 

September 30, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Airplane Certification Service. 

[FR Doc. 05–20267 Filed 10–6–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22624; Directorate 

Identifier 2004–NM–81–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Boeing Model 747 airplanes. This 

proposed AD would require the 

following actions for the drive 

mechanism of the horizontal stabilizer: 

Repetitive detailed inspections for 

discrepancies and loose ball bearings; 

repetitive lubrication of the ballnut and 

ballscrew; repetitive measurements of 

the freeplay between the ballnut and the 

ballscrew; and corrective action if 

necessary. This proposed AD is 

prompted by a report of extensive 

corrosion of a ballscrew in the drive 

mechanism of the horizontal stabilizer 

on a similar airplane model. We are 

proposing this AD to prevent an 

undetected failure of the primary load 

path for the ballscrew in the horizontal 

stabilizer and subsequent wear and 

failure of the secondary load path, 

which could lead to loss of control of 

the horizontal stabilizer and consequent 

loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 21, 

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. 

You can get the service information 

identified in this proposed AD from 

Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. 

You can examine the contents of this 

AD docket on the Internet at http:// 

dms.dot.gov, or at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Room PL–401, on the plaza level 

of the Nassif Building, Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Kelly McGuckin, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Airplane 

Certification Office, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056; 

telephone (425) 917–6490; fax (425) 

917–6590. 

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2005–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2005–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

We invite you to submit any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22624; Directorate Identifier 

2004–NM–81–AD’’ in the subject line 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 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 DOT’s complete Privacy Act 

Statement in the Federal Register 

58624 Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules 

published on April 11, 2000 (65 FR 

19477–78), or you may visit http:// 

dms.dot.gov. 

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications that 

affect you. You can get more 

information about plain language at 

http://www.faa.gov/language and http:// 

www.plainlanguage.gov. 

Examining the Docket 

You can examine the AD docket 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 

On January 31, 2000, there was an 

accident involving a McDonnell Douglas 

Model DC–9–83 (MD–83) airplane. The 

National Transportation Safety Board 

(NTSB) determined that the probable 

cause of this accident was a loss of 

airplane pitch control resulting from the 

in-flight failure of the acme nut threads 

of the jackscrew assembly of the 

horizontal stabilizer trim system. The 

NTSB concluded that the thread failure 

was caused by excessive wear, resulting 

from insufficient lubrication of the 

jackscrew assembly. 

The drive mechanism of the 

horizontal stabilizer on McDonnell 

Douglas Model DC–9–83 (MD–83) 

airplanes has a jackscrew assembly with 

an acme screw. The drive mechanism of 

the horizontal stabilizer on Boeing 

Model 747 airplanes uses a ballscrew. 

Acme screws and ballscrews have some 

differences in design, but perform 

similar functions and have the same 

airplane level effect following failure. 

The manufacturer’s safety analysis of 

the 747 drive mechanism found no 

safety problems with the configuration 

of the drive mechanism, but showed 

that changes to the maintenance 

procedures and maintenance intervals 

are required to keep the drive 

mechanism properly maintained and 

operating as designed. 

We have received a report indicating 

that the ballscrew in the drive 

mechanism of the horizontal stabilizer 

on a Boeing Model 757 series airplane 

showed extensive corrosion, which 

could lead to excessive wear. The 

ballscrew on Boeing Model 757 

airplanes is similar to that on the Boeing 

Model 747 airplanes that are the subject 

of this proposed AD. Therefore, both of 

these airplane models could have the 

same unsafe condition. We are 

considering separate action for Boeing 

Model 757 airplanes and other similar 

Boeing airplanes. 

Extensive corrosion of the ballscrew 

in the drive mechanism of the 

horizontal stabilizer, if not corrected, 

could cause an undetected failure of the 

primary load path for the ballscrew and 

subsequent wear and failure of the 

secondary load path, which could lead 

to loss of control of the horizontal 

stabilizer and consequent loss of control 

of the airplane. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–27A2396, Revision 

1, dated August 4, 2005. 

The compliance times specified in the 

service bulletin is as follows: 

For all airplanes: The compliance 

times for the initial detailed inspections 

and lubrication of the ballnut and 

ballscrew is 15,000 total flight hours or 

18 months after the original issue date 

on the service bulletin, whichever 

occurs later. The inspection is repeated 

at intervals not to exceed between 2,000 

and 4,000 flight hours or 24 months, 

whichever occurs first; the lubrication is 

repeated at intervals not to exceed 2,000 

flight hours or 12 months, whichever 

occurs first. 

For all airplanes except those on 

which an FAA-approved low utilization 

maintenance program is in effect: The 

compliance time for the initial 

ballscrew-to-ballnut freeplay inspection 

is 15,000 flight hours after 

accomplishing the last ballscrew-toballnut freeplay inspection or 18 

months after the original issue date on 

the service bulletin, whichever occurs 

later. If the inspection has never been 

done, the compliance time for the initial 

inspection is 15,000 flight hours after 

the delivery date of the airplane or 18 

months after the original issue date on 

the service bulletin, whichever occurs 

later. The inspection is repeated at 

intervals not to exceed between 18,000 

flight hours and 21,000 flight hours. 

For all airplanes except those on 

which an FAA-approved low utilization 

maintenance program is in effect: The 

compliance time for the initial 

ballscrew-to-ballnut freeplay inspection 

is 60 months after accomplishing the 

last ballscrew-to-ballnut freeplay 

inspection. If the inspection has never 

been done, the compliance time for the 

initial inspection is within 60 months 

after the delivery date of the airplane. 

The inspection is repeated at intervals 

not to exceed 72 months. 

The service bulletin also describes the 

procedures in the following table for the 

drive mechanism of the horizontal 

stabilizer. 

PROCEDURES SPECIFIED IN BOEING ALERT SERVICE BULLETIN 747–27A2396 

Work package Repetitive actions Corrective action 

1 .................... Accomplishing detailed visual inspections for discrepancies (including cracks, corrosion, damage, and worn areas); and a 

detailed inspection for loose ball bearings of the external 

areas of the drive mechanism and areas below the drive 

mechanism.

Replacing the ballscrew actuator with a new or overhaulted actuator if any discrepancy is found during any inspection. 

2 .................... Lubricating the ballnut and ballscrew of the horizontal stabilizer 

drive mechanism.

Not applicable. 

3 .................... Measuring the freeplay between the ballnut and ballscrew ....... Replacing the ballscrew actuator with a new or overhauled actuator if the freeplay is more than the specified limit. 

We have determined that 

accomplishing the actions specified in 

the service bulletin will adequately 

address the unsafe condition. 

The service bulletin refers to the 747 

Airplane Maintenance Manuals (AMM) 

in the following table as additional 

sources of service information for 

accomplishing the detailed inspections, 

lubrications, freeplay measurements, 

and corrective action. 

Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules 58625 

ADDITIONAL SOURCES OF SERVICE

INFORMATION

Boeing AMM Subject 

747–100/200/300 AMM ........ 12–21–19 

747–100/200/300 AMM ........ 27–41–06 

747–400 AMM ...................... 12–21–19 

747–400 AMM ...................... 27–41–06 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other airplanes of this same 

type design. Therefore, we are 

proposing this AD, which would require 

the following actions for the drive 

mechanism of the horizontal stabilizer: 

• Repetitive detailed inspections for 

discrepancies of the ballscrew assembly; 

• Repetitive lubrication of the ballnut 

and ballscrew; 

• Repetitive measurements of 

freeplay between the ballnut and the 

ballscrew; and 

• Corrective action if necessary. 

The proposed AD would require you 

to use the service bulletin described 

previously to perform these actions; 

except as discussed under ‘‘Difference 

Between the Proposed AD and Service 

Information.’’

Differences Between the Proposed AD 

and Service Information 

The service bulletin specifies 

compliance times relative to the date of 

issuance of the service bulletin; 

however, this proposed AD would 

require compliance before the specified 

compliance time after the effective date 

of this AD. 

Costs of Compliance 

This proposed AD would affect about 

1,082 Model 747 series airplanes 

worldwide. The following table 

provides the estimated costs for U.S. 

operators to comply with this proposed 

AD, per cycle. 

ESTIMATED COSTS

Repetitive actions Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Detailed inspection ............................ 1 $65 None .................... $65 236 $15,340 

Lubrication ......................................... 1 65 None .................... 65 236 15,340 

Freeplay measurement ...................... 3 65 None .................... 195 236 46,020 

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 will not have federalism 

implications under Executive Order 

13132. This proposed 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 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. See the ADDRESSES

section for a location to examine the 

regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Airplane, 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 FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Boeing: Docket No. FAA–2005–22624; 

Directorate Identifier 2004–NM–81–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by November 21, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

747–100, 747–100B, 747–100B SUD, –200B, 

747–200C, 747–200F, 747–300, 747–400, 

747–400D, 747–400F, 747SR, and 747SP 

series airplanes; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a report of 

extensive corrosion of a ballscrew in the 

horizontal stabilizer of a similar airplane 

model. We are issuing this AD to prevent an 

undetected failure of the primary load path 

for the ballscrew in the drive mechanism of 

the horizontal stabilizer and subsequent wear 

and failure of the secondary load path, which 

could lead to loss of control of the horizontal 

stabilizer and consequent loss of control 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. 

Repetitive Detailed Inspection/Lubrication/ 

Freeplay Measurement and Corrective 

Action 

(f) Do all the applicable actions, including 

any applicable corrective action, specified in 

Work Packages 1, 2, and 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–27A2396, Revision 1, 

dated August 4, 2005. Do the actions at the 

applicable compliance time specified in 

Table 1 of paragraph 1.E. ‘‘Compliance’’ of 

58626 Federal Register / Vol. 70, No. 194 / Friday, October 7, 2005 / Proposed Rules 

the service bulletin; except, where the service 

bulletin specifies a compliance time relative 

to the original issue date of the service 

bulletin, this AD requires compliance relative 

to the effective date of this AD. Where the 

service bulletin specifies a compliance time 

relative to the delivery date of the airplane, 

this AD requires compliance relative to the 

date of issuance of the original standard 

airworthiness certificate. Do any applicable 

corrective action before further flight. Repeat 

the actions at the applicable repeat interval 

specified in Table 1 of paragraph 1.E 

‘‘Compliance’’ of the service bulletin. 

Note 1: Boeing Alert Service Bulletin 747–

27A2396, Revision 1, dated August 4, 2005, 

refers to the Airplane Maintenance Manuals 

(AMMs) in Table 1 of this AD as additional 

sources of service information for 

accomplishing the detailed visual 

inspections, lubrications, freeplay 

measurements, and corrective actions. 

TABLE 1.—ADDITIONAL SOURCES OF

SERVICE INFORMATION

Boeing AMM Subject 

747–100/200/300 AMM ........ 12–21–19 

747–100/200/300 AMM ........ 27–41–06 

747–400 AMM ...................... 12–21–19 

747–400 AMM ...................... 27–41–06 

Previously Accomplished Actions 

(g) For airplanes on which the drive 

mechanism of the horizontal stabilizer was 

replaced before the effective date of this AD 

with a drive mechanism that was not new or 

overhauled, and the detailed and freeplay 

inspections were not accomplished in 

accordance with Boeing Alert Service 

Bulletin 747–27A2396, dated September 4, 

2003: Within 4,000 flight hours or 24 months 

after the effective date of this AD, whichever 

is first, accomplish the inspections, and 

perform any applicable corrective action 

before further flight, in accordance with 

Work Package 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–27A2396, Revision 1, dated August 4, 

2005. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install on any airplane a 

horizontal stabilizer trim actuator unless it is 

new or has been overhauled in accordance 

with Boeing Alert Service Bulletin 747–

27A2396, Revision 1, dated August 4, 2005; 

or has been inspected, lubricated, and 

measured in accordance with paragraph (f) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, Seattle Airplane 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

Issued in Renton, Washington, on 

September 30, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Airplane Certification Service. 

[FR Doc. 05–20268 Filed 10–6–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22631; Directorate 

Identifier 2005–NM–183–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–120, –120ER, 

–120FC, –120QC, and –120RT 

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 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–120, –120ER, 

–120FC, –120QC, and –120RT airplanes. 

This proposed AD would require 

modifying electrical harnesses located at 

the left- and right-hand wing roots; and 

re-routing and modifying the harness of 

the right-hand outboard flap actuator. 

This proposed AD results from fuel 

system reviews conducted by the 

manufacturer. We are proposing this AD 

to prevent chafed electrical harnesses, 

which could result in a potential source 

of ignition for fuel vapors near a fuel 

tank and consequent fire or fuel tank 

explosion. 

DATES: We must receive comments on 

this proposed AD by November 7, 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 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), P.O. Box 

343—CEP 12.225, Sao Jose dos 

Campos—SP, Brazil, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2474; 

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 in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2005–22631; Directorate 

Identifier 2005–NM–183–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 

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.