70568 Federal Register / Vol. 69, No. 234 / Tuesday, December 7, 2004 / Proposed Rules 

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, 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):

Bombardier, Inc. (Formerly Canadair):

Docket No. FAA–2004–19761; 

Directorate Identifier 2003–NM–167–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by January 6, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

CL–600–2B19 (Regional Jet Series 100 and 

440) airplanes, certificated in any category, as 

identified in Bombardier Service Bulletin 

S.B. 601R–49–015, including Appendix A, 

dated November 6, 1998. 

Unsafe Condition 

(d) This AD is prompted by reports of 

incomplete drainage of the Auxiliary Power 

Unit (APU) enclosure. We are issuing this AD 

to prevent a negative pressure condition from 

developing in the APU enclosure when the 

APU is operating on the ground, which could 

create a potential fire hazard if flammable 

fluid leakage occurs inside the APU 

enclosure and cannot be drained overboard. 

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. 

Modify APU Cooling Air Exhaust 

(f) Within 2,000 flight hours after the 

effective date of the AD, or within 16 months 

after the effective date of this AD, whichever 

occurs first: Modify the APU cooling air 

exhaust by doing all of the actions in the 

Accomplishment Instructions of Bombardier 

Service Bulletin S.B. 601R–49–015, dated 

November 6, 1998, except that submitting a 

comment sheet and a compliance sheet are 

not required by this AD.

Note 1: Bombardier Service Bulletin S.B. 

601R–49–015, dated November 6, 1998, 

refers to Avica Service Bulletin 10S145–49–

01, dated July 15, 1998, and Canadair Kit 

Drawing K601R97150, Rev NC, as additional 

sources of service information for doing the 

modification. The Avica service bulletin and 

the Canadair Kit Drawing are included as 

Appendix A of the Bombardier service 

bulletin.

Parts Installation 

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

person may install an APU enclosure having 

Canadair part number (P/N) 601R97150–13, 

or Avica P/N 15A104–101, on any airplane, 

unless the unit has been modified in 

accordance with paragraph (f) of this AD. 

Alternative Methods of Compliance 

(h) The Manager, New York Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(i) Transport Canada Civil Aviation 

Canadian airworthiness directive CF–2002–

21, dated March 21, 2002, also addresses the 

subject of this AD.

Issued in Renton, Washington, on 

November 26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–26798 Filed 12–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19762; Directorate 

Identifier 2004–NM–168–AD] 

RIN 2120–AA64

Airworthiness Directives; Airbus Model 

A318, A319, A320, and A321 Series 

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 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This proposed 

AD would require an inspection of the 

spoiler servo control for certain part 

numbers and corrective action if 

necessary. This proposed AD is 

prompted by a report of a broken piston 

rod bearing of the spoiler servo control. 

We are proposing this AD to prevent 

breakage of the piston rod bearing, 

which could cause loss of the associated 

hydraulic system and spoiler extension, 

and could result in reduced 

controllability of the airplane.

DATES: We must receive comments on 

this proposed AD by January 6, 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. 

For service information identified in 

this proposed AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 

You can examine the contents of this 

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, on the plaza level of 

the Nassif Building, Washington, DC. 

This docket number is FAA–2004–

19762; the directorate identifier for this 

docket is 2004–NM–168–AD.

FOR FURTHER INFORMATION CONTACT:

Technical information: Dan Rodina, 

Aerospace Engineer, International 

Branch, ANM–116, FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

Federal Register / Vol. 69, No. 234 / Tuesday, December 7, 2004 / Proposed Rules 70569

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–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–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 relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19762; Directorate Identifier 

2004–NM–168–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 

website, 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. 

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 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 A318, A319, 

A320, and A321 series airplanes fitted 

with GOODRICH spoiler actuators part 

number (P/N) 31077–050, –060, –070, 

–110 or –112. The DGAC advises that an 

incorrect manufacturing process 

resulted in the seal groove radii of the 

piston rod bearing of the spoiler servo 

control being smaller than the drawing 

specification. This condition, if not 

corrected, could result in reduced 

fatigue life of the piston rod bearing and 

consequent breakage, which could cause 

loss of the associated hydraulic system 

and spoiler extension, and could result 

in reduced controllability of the 

airplane. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–27–1158; and Service Bulletin 

A320–27–1159; both including 

Appendices 01 and 02; both dated May 

26, 2004. The service bulletins describe 

procedures for inspecting the spoiler 

servo control for part numbers 31077–

050, –060, –070, –110, and –112, and 

corrective action if necessary. The 

corrective action includes replacing the 

spoiler servo control with a new or 

modified spoiler servo control. 

The inspections are to be done at the 

following positions: 

• For Model A318, A319, and A321 

series airplanes: Positions 1 through 5

• For Model A320 series airplanes on 

which Airbus modification 26335 and 

Airbus Service Bulletin A320–27–1115, 

dated October 27, 1997; and Revision 

01, dated June 22, 1999; has not been 

done: Positions 1, 2, and 3

• For Model A320 series airplanes on 

which Airbus modification 26335 or 

Airbus Service Bulletin A320–27–1115, 

dated October 27, 1997; or Revision 01, 

dated June 22, 1999; has been done: 

Positions 1 through 5

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 directive F–2004–122, 

dated July 21, 2004, to ensure the 

continued airworthiness of these 

airplanes in France. 

Airbus Service Bulletins A320–27–

1158 and A320–27–1159, both dated 

May 26, 2004, refer to Goodrich Service 

Bulletin 31077–27–14, dated May 24, 

2004, as an additional source of service 

information for modifying the spoiler 

servo control. 

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 §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 accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between the Proposed AD and the 

Service Bulletins.’’

Differences Between the Proposed AD 

and the Service Bulletins 

Operators should note that Airbus 

Service Bulletin A320–27–1158; and 

Service Bulletin A320–27–1159; both 

dated May 26, 2004; specify to contact 

Goodrich if the part number of the servo 

control is missing. However, this 

proposed AD requires operators to 

replace the spoiler servo control with a 

new or modified spoiler servo control if 

operators are unable to determine the 

part number. 

Although the Accomplishment 

Instructions of Airbus Service Bulletins 

A320–27–1158 and A320–27–1159 

describe procedures for reporting 

certain information to the manufacturer, 

this proposed AD would not require that 

action. 

Clarification of Inspection Type 

Airbus Service Bulletins A320–27–

1158 and A320–27–1159 specify to do a 

‘‘visual inspection’’ to determine the 

part number of the spoiler servo 

controls. This proposed AD would 

require a ‘‘general visual inspection’’ for 

these actions. We have included the 

definition for a general visual inspection 

in a note in this proposed AD. 

Differences Between the Proposed AD 

and French Airworthiness Directive 

French airworthiness directive F–

2004–122, dated July 21, 2004, has an 

effectivity of ‘‘AIRBUS A318, A319, 

70570 Federal Register / Vol. 69, No. 234 / Tuesday, December 7, 2004 / Proposed Rules 

A320 and A321 aircraft, all certified 

models, all serials numbers, fitted with 

GOODRICH spoiler actuators P/N 

31077–050, –060, –070, –110 or –112.’’

However, because spoiler actuators are 

interchangeable on Airbus Model A318, 

A319, A320, and A321 series airplanes, 

airplanes not fitted with the spoiler 

actuators P/N 31077–050, –060, –070, 

–110 or ‘‘112 may have a spoiler 

actuator P/N 31077–050, –060, –070, 

–110 or ‘‘112 installed in the future by 

operators during normal maintenance. 

Therefore, the applicability of this 

proposed AD includes all Airbus Model 

A318, A319, A320, and A321 series 

airplanes. Both the proposed AD and 

French airworthiness directive require 

an inspection for the part number of the 

spoiler actuator (spoiler servo control). 

Clarification of Actions in Proposed AD 

and the Service Bulletins 

Although the Accomplishment 

Instructions of Airbus Service Bulletin 

A320–27–1158 do not specify 

procedures for Model A318 and A319 

series airplanes, those models are 

specified in the Reason/Description/

Operational Consequences section of the 

service bulletin, which recommends 

inspecting positions 2, 3, 4, and 5 for 

those models. Those models are also 

specified in the note within the 

Effectivity, section 1.A., of the service 

bulletin. This proposed AD would 

require inspections for Model A318 and 

A319 series airplanes at positions 2, 3, 

4, and 5; and corrective actions if 

necessary. 

Although the Accomplishment 

Instructions of Airbus Service Bulletin 

A320–27–1159 do not specify 

procedures for Model A318 and A319 

series airplanes, those models are 

specified in the Reason/Description/

Operational Consequences section of the 

service bulletin, which recommends 

inspecting position 1 for those models. 

Those models are also specified in the 

note within the Effectivity, section 1.A., 

of the service bulletin. This proposed 

AD would require inspections for Model 

A318 and A319 series airplanes at 

position 1 and corrective actions if 

necessary. 

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 

Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection ................................................................. 3–5 $65 $195–$325 648 $126,360–$210,600

Authority for this Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. 

This rulemaking is promulgated 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701, ‘‘General requirements.’’ Under 

that section, the FAA is charged 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 proposed AD. 

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. 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 FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

Airbus: Docket No. FAA–2004–19762; 

Directorate Identifier 2004–NM–168–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

January 6, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A318, A319, A320, and A321 series 

airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a report of 

a broken piston rod bearing of the spoiler 

servo control. We are issuing this AD to 

prevent breakage of the piston rod bearing, 

which could cause loss of the associated 

hydraulic system and spoiler extension, and 

could result in reduced controllability 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. 

Phase 1 Inspection 

(f) Within 12 months after the effective 

date of this AD, do a general visual 

inspection for the part number of the spoiler 

servo control at the applicable locations 

specified in Table 1 of this AD, in accordance 

with Airbus Service Bulletin A320–27–1158, 

including Appendices 01 and 02, dated May 

26, 2004.

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 

Federal Register / Vol. 69, No. 234 / Tuesday, December 7, 2004 / Proposed Rules 70571

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 normal 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.’’

TABLE 1.—PHASE 1 SPOILER SERVO CONTROL INSPECTION

For Airbus model— Inspect spoiler servo controls at—

A318 and A319 series airplanes .............................................................. Positions 2, 3, 4, and 5. 

A320 series airplanes ............................................................................... Position 2. 

A321 series airplanes ............................................................................... Positions 2, 3, and 4. 

Phase 2 Inspection 

(g) Within 30 months after the effective 

date of this AD, do a general visual 

inspection for the part number of the spoiler 

servo control at the applicable locations 

specified in Table 2 of this AD, in accordance 

with Airbus Service Bulletin A320–27–1159, 

including Appendix 01 and 02, dated May 

26, 2004.

TABLE 2.—PHASE 2 SPOILER SERVO CONTROL INSPECTION

For Airbus model— Inspect spoiler servo controls at—

A318 and A319 series airplanes ..................................................................................................... Position 1. 

A320 series airplanes on which Airbus modification 26335 and Airbus Service Bulletin A320–

27–1115, dated October 27, 1997; and Revision 01, dated June 22, 1999; has not been 

done.

Positions 1 and 3. 

A320 series airplanes on which Airbus modification 26335 or Airbus Service Bulletin A320–27–

1115, dated October 27, 1997; or Revision 01, dated June 22, 1999; has been done.

Positions 1, 3, 4, and 5. 

A321 series airplanes ..................................................................................................................... Positions 1 and 5. 

Corrective Action 

(h) If, during any inspection specified in 

paragraph (f) or (g) of this AD, part number 

(P/N) 31077–050, –060, –070, –110, or –112 

is found or if unable to determine the P/N, 

before further flight, replace the spoiler servo 

control with a new or modified spoiler servo 

control, in accordance with Airbus Service 

Bulletin A320–27–1158; or Airbus Service 

Bulletin A320–27–1159; both including 

Appendices 01 and 02; both dated May 26, 

2004; as applicable.

Note 2: Airbus Service Bulletins A320–27–

1158 and A320–27–1159 refer to Goodrich 

Service Bulletin 31077–27–14, dated May 24, 

2004, as an additional source of service 

information for modifying the spoiler servo 

control.

Reporting Not Required 

(i) Although Airbus Service Bulletins 

A320–27–1158 and A320–27–1159 specify to 

submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Parts Installation 

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

person may install a spoiler servo control, P/

N 31077–050, –060, –070, –110, or –112, on 

any airplane, unless it has been modified 

according to Airbus Service Bulletin A320–

27–1158; or Airbus Service Bulletin A320–

27–1159; both including Appendices 01 and 

02; both dated May 26, 2004. 

Alternative Methods of Compliance 

(AMOCs) 

(k) 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. 

Related Information 

(l) French airworthiness directive F–2004–

122, dated July 21, 2004, also addresses the 

subject of this AD.

Issued in Renton, Washington, on 

November 26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–26797 Filed 12–6–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19763; Directorate 

Identifier 2004–NM–187–AD] 

RIN 2120–AA64

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) 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 

certain Bombardier Model CL–600–

2B19 (Regional Jet Series 100 & 440) 

airplanes. This proposed AD would 

require doing repetitive inspections for 

fractures and cracks of the links of the 

aileron power control unit (PCU); 

replacing any fractured/cracked link; 

and doing applicable related 

investigative and corrective actions, if 

necessary. This proposed AD is 

prompted by reports indicating that the 

links of the aileron PCU have failed. We 

are proposing this AD to prevent failure 

of both links of the aileron PCU, which 

could result in reduced lateral control of 

the airplane.

DATES: We must receive comments on 

this proposed AD by January 6, 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. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., Canadair, Aerospace Group, P.O. 

Box 6087, Station Centre-ville, 

Montreal, Quebec H3C 3G9, Canada.