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. 

70572 Federal Register / Vol. 69, No. 234 / Tuesday, December 7, 2004 / Proposed Rules 

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–

19763; the directorate identifier for this 

docket is 2004–NM–187–AD.

FOR FURTHER INFORMATION CONTACT:

Technical information: Dan Parrillo, 

Aerospace Engineer, Systems and Flight 

Test Branch, ANE–172, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Westbury, suite 410, 

New York 11590; telephone (516) 228–

7305; fax (516) 794–5531. 

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 

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–

2004–19763; Directorate Identifier 

2004–NM–187–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 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, notified us that an 

unsafe condition may exist on certain 

Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. TCCA advises that it has 

received reports indicating that the links 

of the aileron power control unit (PCU) 

have failed on several in-service 

airplanes. Failure of one link is 

considered to be a dormant failure. 

Failure of both links, if not corrected, 

could result in reduced lateral control of 

the airplane. 

Relevant Service Information 

Bombardier has issued Alert Service 

Bulletin A601R–27–130, Revision ‘‘B,’’

including Appendices A and B, dated 

May 11, 2004. The service bulletin 

describes procedures for doing 

repetitive detailed inspections for 

fractures and cracks of the links of the 

aileron PCU; replacing any fractured/

cracked link; and doing applicable 

related investigative and corrective 

actions, if necessary. The related 

investigative/corrective actions include: 

• Recording the torque value of the 

forward and aft attachment bolts for 

both links of the applicable aileron PCU; 

• Checking for mismatch between the 

link and output fork of aileron PCU; and 

• Doing an eddy current inspection of 

the lugs of the aileron PCU, and 

contacting the airplane manufacturer if 

a crack is found. 

The service bulletin also describes 

procedures for submitting inspection 

findings and other information to the 

airplane manufacturer. 

TCAA mandated the service 

information and issued Canadian 

airworthiness directive CF–2004–13, 

dated July 20, 2004, to ensure the 

continued airworthiness of these 

airplanes in Canada. 

FAA’s Determination and Requirements 

of the Proposed AD 

This airplane model is manufactured 

in Canada and is 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, 

TCCA has kept the FAA informed of the 

situation described above. We have 

examined TCCA’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 AD and Service Bulletin.’’

Differences Between Proposed AD and 

Service Bulletin 

The service bulletin specifies that you 

may contact the manufacturer for 

disposition of any cracked aileron lug, 

but this proposed AD would require you 

to disposition and replace any cracked 

aileron lug using a method that we or 

TCCA (or its delegated agent) approve. 

In light of the type of replacement that 

would be required to address the unsafe 

condition, and consistent with existing 

bilateral airworthiness agreements, we 

have determined that, for this proposed 

AD, a replacement we or TCCA approve 

would be acceptable for compliance 

with this proposed AD. 

Operators should note that, although 

the Accomplishment Instructions of the 

referenced service bulletin describe 

procedures for submitting a comment 

sheet related to service bulletin quality 

and a sheet recording compliance with 

the service bulletin, this proposed AD 

would not require those actions. We do 

not need this information from 

operators. 

Interim Action 

This is considered to be interim 

action until final action is identified, at 

Federal Register / Vol. 69, No. 234 / Tuesday, December 7, 2004 / Proposed Rules 70573

which time we may consider further 

rulemaking. 

Costs of Compliance 

This proposed AD would affect about 

697 airplanes of U.S. registry. The 

proposed inspection would take about 1 

work hour per airplane, at an average 

labor rate of $65 per work hour. Based 

on these figures, the estimated cost of 

the proposed AD for U.S. operators is 

$45,305, or $65 per airplane, per 

inspection cycle. 

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):

Bombardier, Inc. (Formerly Canadair):

Docket No. FAA–2004–19763; 

Directorate Identifier 2004–NM–187–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 Bombardier Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, serial numbers 7003 and 

subsequent; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by reports 

indicating that the links of the aileron power 

control unit (PCU) have failed. We are 

issuing this AD to prevent failure of both 

links of the aileron PCU, which could result 

in reduced lateral 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 Inspections 

(f) Before the accumulation of 2,000 total 

flight hours, or within 550 flight hours after 

the effective date of this AD, whichever 

occurs later, do a detailed inspection for 

fractures and cracks of the links of the aileron 

PCU, in accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A601R–27–130, 

Revision ‘‘B,’’ including Appendices A and 

B, dated May 11, 2004. Repeat the detailed 

inspection thereafter at intervals not to 

exceed 1,000 flight hours.

Note 1: For the purposes of this AD, a 

detailed inspection is ‘‘an intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirrors magnifying 

lenses, etc. may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Corrective Action 

(g) If any fractured or cracked link is 

detected during any inspection required by 

paragraph (f) of this AD, before further flight, 

replace the fractured/cracked link and do the 

applicable related investigative and 

corrective actions by doing all the actions in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A601R–27–130, 

Revision ‘‘B,’’ including Appendices A and 

B, dated May 11, 2004; except as required by 

paragraph (h) of this AD. 

(h) If any crack is found on the aileron lugs 

during any related investigative action 

required by paragraph (g) of this AD, and the 

service bulletin recommends contacting 

Bombardier for disposition: Before further 

flight, disposition and replace the cracked 

aileron lug in accordance with a method 

approved by the Manager, New York Aircraft 

Certification Office (ACO), FAA, or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent). 

Acceptable Revisions of the Referenced 

Service Bulletin 

(i) Actions specified in paragraphs (f) and 

(g) of this AD done before the effective date 

of this AD in accordance with Bombardier 

Alert Service Bulletin A601R–27–130, 

Revision ‘‘A,’’ including Appendices A and 

B, dated December 22, 2003; are acceptable 

for compliance with the corresponding 

requirements of paragraphs (f) and (g) of this 

AD. 

(j) Accomplishment of the initial 

inspection of the links of the aileron PCU, 

and replacement if necessary, before the 

effective date of this AD in accordance with 

Bombardier Alert Service Bulletin A601R–

27–130, including Appendices A and B, 

dated November 13, 2003, is acceptable for 

compliance with the corresponding 

requirements of paragraphs (f) and (g) of this 

AD; except as provided by paragraph (k) of 

this AD. 

(k) Airplanes on which a fractured or 

cracked link of the aileron PCU was found 

that were not subject to an NDT inspection 

of the aileron lugs (i.e., related investigative 

action required by paragraph (h) of this AD) 

before the effective date of this AD must do 

an NDT inspection of the applicable lugs in 

accordance with paragraph (g) of this AD at 

the next repetitive detailed inspection of the 

link of the aileron PCU required by this AD. 

Reporting 

(l) Submit a report of the findings (both 

positive and negative) of the initial 

inspection required by paragraph (f) of this 

AD and any associated fractured or cracked 

link to Bombardier Aerospace Inc., c/o InService Engineering, 3rd floor, Dept. 508, 400 

Cote Vertu Road West, Dorval, QC, Canada 

H4S 1Y9, at the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD. The 

report must be done in accordance with 

Appendices A and B of Bombardier Alert 

Service Bulletin A601R–27–130, Revision 

‘‘B,’’ dated May 11, 20004. Under the 

provisions of the Paperwork Reduction Act of 

1980 (44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done after the 

effective date of this AD: Submit the report 

and any fractured/cracked link within 30 

days after the inspection. 

(2) If the inspection was accomplished 

prior to the effective date of this AD: Submit 

the report and any fractured/cracked link 

within 30 days after the effective date of this 

AD. 

No Submission of Comment Sheets 

(m) Although the service bulletin 

referenced in this AD specifies to submit 

comment and compliance sheets to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(n) The Manager, New York 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. 

70574 Federal Register / Vol. 69, No. 234 / Tuesday, December 7, 2004 / Proposed Rules 

Related Information 

(o) Canadian airworthiness directive CF–

2004–13, dated July 20, 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. 04–26796 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–2004–19764; Directorate 

Identifier 2004–NM–02–AD] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 777–200 and –300 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 

certain Boeing Model 777–200 and –300 

series airplanes. This proposed AD 

would require applying an anti-static 

conductive coating to the fuel access 

and thermal anti-icing blowout doors at 

the location of the bonding fasteners on 

the leading edge of the wings, and 

performing a resistance test on the new 

coating to ensure correct ground path 

resistance. This proposed AD is 

prompted by a report that an anti-static 

coating was not applied correctly on 

doors located within a flammable fluid 

leakage zone. We are proposing this AD 

to prevent an uncontrollable fire in the 

leading edge of the wing, which could 

damage critical wing structures and 

cause a fuel tank explosion.

DATES: We must receive comments on 

this proposed AD by January 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. 

For service information identified in 

this proposed AD, contact 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 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.

FOR FURTHER INFORMATION CONTACT:

Technical information: Margaret 

Langsted, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6500; fax (425) 917–6590. 

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 

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–

2004–19764; Directorate Identifier 

2004–NM–02–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 

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 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 athttp://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 

We have received a report indicating 

that, during production, an anti-static 

coating was not applied correctly on 

fuel access and thermal anti-icing 

blowout doors at the location of the 

bonding fasteners on the leading edge of 

the wings on certain Boeing Model 777–

200 and –300 series airplanes. The antistatic coating is necessary to help ensure 

an electrical bond ground path at the 

doors, which are located within a 

flammable fluid leakage zone. Without 

the anti-static coating, a static charge 

may build up and provide an ignition 

source for flammable vapors when the 

static discharges. This condition, if not 

corrected, could result in an 

uncontrollable fire in the leading edge 

of the wing, which could damage 

critical wing structures and cause a fuel 

tank explosion. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 777–57–

0046, dated September 25, 2003. The 

service bulletin describes procedures for 

applying an anti-static conductive 

coating on the fuel access and thermal