5078 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 

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. 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):

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER): Docket No. FAA–2005–

20223; Directorate Identifier 2004–NM–

193–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

March 3, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model EMB–135 and 

–145 series airplanes, certificated in any 

category; as listed in EMBRAER Service 

Bulletin 145–32–0091, Change 01, dated July 

1, 2004. 

Unsafe Condition 

(d) This AD was prompted by a report of 

a fractured axle of the trailing arm of the 

main landing gear (MLG) due to corrosion of 

the axle. We are issuing this AD to prevent 

a broken trailing arm and consequent failure 

of the MLG, which could lead to loss of 

control and damage to the airplane during 

take-off or landing. 

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) Within 600 flight hours or 180 days after 

the effective date of this AD, whichever 

occurs first, perform a detailed inspection for 

surface bruising of the MLG trailing arms and 

integrity of the MLG pivot axle sealant; in 

accordance with the Accomplishment 

Instructions of EMBRAER Service Bulletin 

145–32–0091, Change 01, dated July 1, 2004. 

If no sign of sealant failure or bruising of the 

trailing arm is found, repeat the inspection 

thereafter at intervals not to exceed 5,500 

flight hours or 24 months, whichever occurs 

first, until paragraph (g)(3) of this AD has 

been accomplished.

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 mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Corrective/Terminating Actions 

(g) If any sign of sealant failure or bruising 

of either trailing arm surface is found, prior 

to further flight, do paragraphs (g)(1), (g)(2) 

and (g)(3) of this AD. Do the actions in 

accordance with EMBRAER Service Bulletin 

145–32–0091, Change 01, dated July 1, 2004. 

Accomplishment of paragraphs (g)(2) and 

(g)(3) of this AD ends the repetitive 

inspections required by paragraph (f) of this 

AD. 

(1) Repair any bruising of the trailing arm 

surface. 

(2) Replace the MLG cardan with a new, 

improved cardan. 

(3) Perform a detailed inspection for 

corrosion of the internal surface of the 

trailing arm pivot axle. 

(i) If no corrosion is found, apply 

protective paint and corrosion inhibitors. 

(ii) If corrosion is found, replace the pivot 

axle with a new pivot axle and apply 

corrosion inhibitors.

Note 2: EMBRAER Service Bulletin 145–

32–0091, Change 01, dated July 1, 2004, 

refers to Embraer Liebherr Equipamentos do 

Brasil S.A. (ELEB) Service Bulletin 2309–

2002–32–04, Revision 01, dated May 24, 

2004, as an additional source of service 

information for the inspection and repair of 

the MLG components. The ELEB service 

bulletin is included within the EMBRAER 

service bulletin.

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(h) Actions accomplished before the 

effective date of this AD according to 

EMBRAER Service Bulletin 145–32–0091, 

dated February 19, 2004, are considered 

acceptable for compliance with the 

corresponding actions specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i) 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 

(j) Brazilian airworthiness directive 2004–

08–02, dated September 3, 2004, also 

addresses the subject of this AD.

Issued in Renton, Washington, on January 

21, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–1807 Filed 1–31–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20222; Directorate 

Identifier 2004–NM–230–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315 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 DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. The subject of this 

proposed AD is the pilot’s static system. 

This proposed AD would require 

Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 5079

revising the airplane flight manual to 

include applicable procedures to follow 

when the flightcrew receives abnormal 

indications of airspeed, altitude, or 

vertical airspeed. This proposed AD 

would also require modifying the static 

system. This proposed AD is prompted 

by a report of a leak in the static 

pressure system, which could result in 

loss of the static systems and 

consequent erroneous data displayed on 

the pilot’s flight instruments. We are 

proposing this AD to advise the 

flightcrew of applicable procedures in 

the event of abnormal indications of 

airspeed, altitude, or vertical airspeed; 

and to prevent leaks in the static system, 

which could result in the loss of critical 

flight information that could result in 

reduced controllability of the airplane 

or controlled flight into terrain.

DATES: We must receive comments on 

this proposed AD by March 3, 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., Bombardier Regional Aircraft 

Division, 123 Garratt Boulevard, 

Downsview, Ontario M3K 1Y5, Canada. 

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–2005–

20222; the directorate identifier for this 

docket is 2004–NM–230–AD.

FOR FURTHER INFORMATION CONTACT: Ezra 

Sasson, 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) 228–7320; 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 under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–20222; Directorate Identifier 

2004–NM–230–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 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, notified the FAA 

that an unsafe condition may exist on 

certain Bombardier Model DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. TCCA advises that an 

investigation of an incident involving 

erroneous data displayed on the pilot’s 

flight instruments has revealed that a 

leak in the pilot’s side static pressure 

system, downstream of the alternate 

selector valve, could result in the loss of 

both the pilot’s normal and alternate 

static systems. This condition, if not 

corrected, could result in the display of 

abnormal indications of airspeed, 

altitude, or vertical airspeed due to 

leaks in the static system and prolonged 

loss of critical flight information that 

could result in reduced controllability 

of the airplane or controlled flight into 

terrain. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 8–34–221, Revision ‘A,’ dated 

September 15, 2003. The service 

bulletin describes procedures to modify 

the pilot’s side static system to prevent 

leaks in the system. For certain 

airplanes the modification provides 

increased independence of the static 

pressure source for the pilot’s primary 

and standby flight instruments, and for 

certain other airplanes the modification 

corrects the length of the static system 

hose. 

TCCA mandated the service bulletin 

and issued Canadian airworthiness 

directive CF–2003–25, dated October 

10, 2003, to ensure the continued 

airworthiness of these airplanes in 

Canada. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in Canada 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, 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 issuing this AD to 

provide procedures to the flightcrew in 

the event of abnormal indications of 

airspeed, altitude, or vertical airspeed; 

and to prevent leaks in the static system, 

which could result in the loss of critical 

flight information that could result in 

reduced controllability of the airplane 

or controlled flight into terrain. This AD 

requires accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Canadian 

Airworthiness Directive.’’

Differences Between the Proposed AD 

and Canadian Airworthiness Directive 

This proposed AD advises revising 

the applicable de Havilland Dash 8 

airplane flight manual to incorporate the 

text specified in paragraph (f) of this 

5080 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 

proposed AD. The Canadian AD does 

not include such a requirement. In 

Canada, operators are mandated to use 

the latest flight manual and therefore, 

TCCA is not required to issue an AD to 

require flight manual revisions. 

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 perairplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Revise AFM ........................ 1 $65 None ................................... $65 181 $11,765 

Modify static system ........... 2 65 100–200 .............................. 230–330 181 41,630–59,730 

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, 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 

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):

Bombardier, Inc. (Formerly de Havilland, 

Inc.): Docket No. FAA–2005–20222; 

Directorate Identifier 2004–NM–230–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

March 3, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes, certificated in any 

category; serial numbers 003 through 598 

inclusive. 

Unsafe Condition 

(d) This AD was prompted by a report of 

a leak in the static pressure system, which 

could result in loss of the static systems and 

consequent erroneous data displayed on the 

pilot’s flight instruments. The subject of this 

AD is the pilot’s static system. We are issuing 

this AD to advise the flightcrew of applicable 

procedures in the event of abnormal 

indications of airspeed, altitude, or vertical 

airspeed; and to prevent leaks in the static 

system, which could result in the loss of 

critical flight information that could result in 

reduced controllability of the airplane or 

controlled flight into terrain. 

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. 

Revision to Airplane Flight Manual 

(f) Within 10 days after the effective date 

of this AD, revise the Normal and Abnormal 

Procedures sections of the applicable de 

Havilland Dash 8 flight manual to include 

the following statement in paragraph 4.11.1 

of 4.11 Pitot—Static and Stall Warning 

System Failures. This may be done by 

inserting a copy of this AD in the applicable 

flight manual.

‘‘4.11.1 ABNORMAL INDICATIONS OF 

AIRSPEED, ALTITUDE AND VERTICAL 

AIRSPEED. 

‘‘1. Appropriate STATIC SOURCE 

selector—ALTERNATE. If switching the 

STATIC SOURCE selector to ALTERNATE 

does not correct the abnormal indications: 

‘‘2. Rely on the flight instruments on the 

opposite side and land as soon as 

practicable.’’

Note 1: When a statement identical to that 

in paragraph (f) of this AD has been included 

in the general revisions of the applicable 

flight manual, the general revisions may be 

inserted into the flight manual, and the copy 

of this AD may be removed from the flight 

manual.

Modification of the Static System 

(g) For airplanes having serial numbers 003 

through 590 inclusive: Within 24 months 

after the effective date of this AD, modify the 

static system in accordance with Part A and 

Part C of the Accomplishment Instructions of 

Bombardier Service Bulletin 8–34–221, 

Revision ‘A,’ dated September 15, 2003. 

(h) For airplanes having serial numbers 591 

through 598 inclusive: Within 24 months 

after the effective date of this AD, modify the 

static system in accordance with Part B and 

Part C of the Accomplishment Instructions of 

Bombardier Service Bulletin 8–34–221, 

Revision ‘A,’ dated September 15, 2003. 

Modifications Done According to Previous 

Issue of Service Bulletin 

(i) Modifications done before the effective 

date of this AD in accordance with 

Bombardier Service Bulletin 8–34–221, dated 

May 27, 2003, are acceptable for compliance 

with the applicable modifications specified 

in paragraphs (g) and (h) of this AD. 

Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 5081

Alternative Methods of Compliance 

(AMOCs) 

(j) The Manager, New York Aircraft 

Certification Office, 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 

(k) Canadian airworthiness directive CF–

2003–25, dated October 10, 2003, also 

addresses the subject of this AD.

Issued in Renton, Washington, on January 

21, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–1808 Filed 1–31–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20220; Directorate 

Identifier 2004–NM–152–AD] 

RIN 2120–AA64 

Airworthiness Directives; Aerospatiale 

Model ATR42–200, –300, and –320 

Series 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 Aerospatiale Model ATR42–200, 

–300, and –320 series airplanes. This 

proposed AD would require doing 

repetitive inspections of the upper arms 

of the MLG side braces for missing or 

inadequately bonded identification 

plates; replacing the upper arm if 

necessary; and replacing the side brace 

assembly with a modified part. This 

proposed AD is prompted by an 

operator who reported experiencing an 

unlock warning for the MLG on the right 

side of the airplane. We are proposing 

this AD to prevent cracking of the upper 

arms of the side braces of the MLG, 

which could result in failure of the MLG 

during landing and possible damage to 

the airplane and injury to the flightcrew 

and passengers.

DATES: We must receive comments on 

this proposed AD by March 3, 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 MessierDowty, BP 10, 78142 Velizy 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–2005–

20220; the directorate identifier for this 

docket is 2004–NM–152–AD.

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

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–

2005–20220; Directorate Identifier 

2004–NM–152–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 certain Aerospatiale Model 

ATR42–200, –300, and –320 series 

airplanes. The DGAC advises that an 

operator reported experiencing, during 

taxiing, an unlock warning for the MLG 

on the right side of the airplane. 

Investigation found that the upper side 

brace of the right MLG was cracked due 

to accidental damage caused by the 

location of certain identification plates 

and possible corrosion introduced 

during production. Cracking of the 

upper arms of the side braces of the 

MLG, if not corrected, could result in 

failure of the MLG during landing and 

possible damage to the airplane and 

injury to the flightcrew and passengers. 

Relevant Service Information 

Messier-Dowty has issued Special 

Inspection Service Bulletin 631–32–175, 

dated January 7, 2004; and Service 

Bulletin 631–32–176, Revision 1, dated 

June 2, 2004. Special Inspection Service 

Bulletin 631–32–175 describes 

procedures for doing repetitive general 

visual inspections of the upper arms of 

the MLG side braces for missing or 

inadequately bonded identification 

plates having P/Ns D61565–1, D61566–

1, D61567–1, and D61568–1; and 

replacing any upper arm having a 

missing or inadequately-bonded 

identification plate with a serviceable 

upper arm having the same part 

number. Service Bulletin 631–32–176 

describes procedures for removing the 

side brace assembly and replacing it 

with a modified part. Modification of 

the side brace assembly includes the 

following actions: