5756 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

(c) A warning in the main passenger cabin. This warning must be readily detectable by a flight attendant, taking into consideration the positioning of flight attendants throughout the main passenger compartment during various phases of flight. 3 Liner

If it can be shown that the material used to construct the stowage compartment meets the flammability requirements of a liner for a Class B 

cargo compartment (i.e., § 25.855 at Amendment 25–93, and Appendix F, part I, paragraph (a)(2)(ii)), then no liner would be required for enclosed stowage compartments equal to or greater than 25 ft3 in interior volume but less than 57 ft3 in interior volume. For all enclosed stowage 

compartments equal to or greater than 57 ft3 in interior volume but less than or equal to 200 ft3, a liner must be provided that meets the requirements of § 25.855 for a Class B cargo compartment. 4 Location Detector

OHCR compartments that contain enclosed stowage compartments exceeding 25 ft3 in interior volume and are located away from one central 

location such as the entry to the OHCR compartment or a common area within the OHCR compartment would require additional fire protection 

features and/or devices to assist the firefighter in determining the location of a fire. 

Issued in Renton, Washington, on January 

26, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2436 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–CE–54–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Cessna 

Aircraft Company Model 525 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2003–21–07, which applies to certain 

The Cessna Aircraft Company (Cessna) 

Model 525 airplanes. AD 2003–21–07 

currently requires you to disengage the 

pitch trim circuit breaker and AP servo 

circuit breaker and then tie strap each 

of them to prevent them from being 

engaged. Not utilizing this equipment 

prevents a single-point failure. This 

proposed AD is the result of Cessna 

having now developed and made 

changes in the design of the affected 

trim printed circuit board (PCB) 

assembly to allow the use of the 

assembly and the prevention of the 

single-point failure, and identification 

of additional airplanes that have the 

same unsafe condition. Consequently, 

this proposed AD would require you to 

remove and replace an old trim PCB 

assembly with a new design assembly or 

modify an old trim PCB assembly to the 

new design. We are issuing this 

proposed AD to correct this single-point 

failure in the electric pitch trim system, 

which will result in a runaway pitch 

trim condition where the pilot could not 

disconnect using the control wheel 

autopilot/trim disconnect switch. 

Failure of the electric trim system 

would result in a large pitch mistrim 

and would cause excessive control 

forces that the pilot could not overcome.

DATES: We must receive any comments 

on this proposed AD by April 15, 2004.

ADDRESSES: Use one of the following to 

submit comments on this proposed AD: 

• By mail: FAA, Central Region, 

Office of the Regional Counsel, 

Attention: Rules Docket No. 2003–CE–

54–AD, 901 Locust, Room 506, Kansas 

City, Missouri 64106. 

• By fax: (816) 329–3771. 

• By e-mail: 9-ACE-7-Docket@faa.gov.

Comments sent electronically must 

contain ‘‘Docket No. 2003–CE–54–AD’’

in the subject line. If you send 

comments electronically as attached 

electronic files, the files must be 

formatted in Microsoft Word 97 for 

Windows or ASCII. 

You may get the service information 

identified in this proposed AD from The 

Cessna Aircraft Company, Product 

Support, P.O. Box 7706, Wichita, 

Kansas 67277; telephone: (316) 517–

6000; facsimile: (316) 517–8500. 

You may view the AD docket at FAA, 

Central Region, Office of the Regional 

Counsel, Attention: Rules Docket No. 

2003–CE–54–AD, 901 Locust, Room 

506, Kansas City, Missouri 64106. Office 

hours are 8 a.m. to 4 p.m., Monday 

through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Dan 

Withers, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, 1801 

Airport Road, Wichita, Kansas 67209; 

telephone: (316) 946–4196; facsimile: 

(316) 946–4107.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

How do I comment on this proposed 

AD? We invite you to submit any 

written relevant data, views, or 

arguments regarding this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘AD Docket 

No. 2003–CE–54–AD’’ in the subject 

line of your comments. If you want us 

to acknowledge receipt of your mailed 

comments, send us a self-addressed, 

stamped postcard with the docket 

number written on it. We will datestamp your postcard and mail it back to 

you. 

Are there any specific portions of this 

proposed AD I should pay attention to?

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this proposed AD. If you contact us 

through a nonwritten communication 

and that contact relates to a substantive 

part of this proposed AD, we will 

summarize the contact and place the 

summary in the docket. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD in light of those comments 

and contacts. 

Discussion 

Has FAA taken any action to this 

point? A report of an accident involving 

a Cessna Model 525 airplane where the 

pilot reported a problem with the pitch 

trim system, and later Cessna and FAA 

analysis that revealed the potential for 

a single-wire shorting caused us to issue 

AD 2003–21–07, Amendment 39–13342 

(68 FR 60028, October 21, 2003). AD 

2003–21–07 currently requires you to do 

the following on Cessna Model 525 

airplanes:

—Disengage the pitch trim circuit 

breaker and AP servo circuit breaker; 

and 

—Tie strap each of them to prevent 

them from being engaged.

What has happened since AD 2003–

21–07 to initiate this proposed action?

AD 2003–21–07 is considered an 

interim action since compliance 

corrected the condition where the 

control wheel autopilot/trim disconnect 

switch did not stop the runaway 

condition. However, AD 2003–21–07 

did not correct the issue of the singlepoint failure while still utilizing the 

desired equipment. Cessna has now 

developed and made changes in the 

design of the affected trim printed 

circuit board (PCB) assembly to 

eliminate the single-point failure while 

allowing the use of the equipment, and 

identified additional airplanes that have 

the same unsafe condition.

What is the potential impact if FAA 

took no action? Failure of the electric 

trim system would result in a large pitch 

mistrim and would cause excessive 

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5757

control forces that the pilot could not 

overcome. 

Is there service information that 

applies to this subject? Cessna has 

issued Citation Service Bulletin No. 

SB525–27–17, dated December 9, 2003. 

What are the provisions of this service 

information? The service bulletin 

includes procedures for:

—Inspecting the electric elevator trim 

motor; 

—Removing the trim PCB assembly; 

—Modifying the trim PCB assembly; 

—Installing a trim PCB assembly; and 

—Removing any tie straps or extension 

caps installed on the AP servos and 

pitch trim circuit breakers. 

FAA’s Determination and Requirements 

of This Proposed AD 

What has FAA decided? We have 

evaluated all pertinent information and 

identified an unsafe condition that is 

likely to exist or develop on other 

products of this same type design. 

Therefore, we are proposing AD action. 

What would this proposed AD 

require? This proposed AD would 

supersede AD 2003–21–07 with a new 

AD that would require you to:

—Remove any 6518351–3 or 6518351–

5 trim PCB assembly and replace with 

a 6518351–10 (EX) trim PCB 

assembly; or 

—Modify the 6518351–8 trim PCB 

assembly to a 6518351–10 trim PCB 

assembly.

How does the revision to 14 CFR part 

39 affect this proposed AD? On July 10, 

2002, we published a new version of 14 

CFR part 39 (67 FR 47997, July 22, 

2002), which governs FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes would this 

proposed AD impact? We estimate that 

this proposed AD affects 251 airplanes 

in the U.S. registry. 

What would be the cost impact of this 

proposed AD on owners/operators of the 

affected airplanes? We estimate the 

following costs to accomplish this 

proposed modification of the 6518351–

8 trim PCB assembly to a 6518351–10 

trim PCB assembly. We have no way of 

determining the number of airplanes 

that may need this modification:

Labor cost Parts cost Total cost per airplane 

4 workhours × $65 per hour = $260 ................................................................................................ $2,995. $2,995+$260 = $3,255. 

We estimate the following costs to 

accomplish this proposed replacement 

of any 6518351–3 or 6518351–5 trim 

PCB assembly with a 6518351–10 (EX) 

trim PCB assembly. We have no way of 

determining the number of airplanes 

that may need this replacement:

Labor cost Parts cost Total cost per airplane 

2 workhours × $65 per hour = $130 ................................................................................................ $2,995. $2,995+$130 = $3,125. 

What is the difference between the 

cost impact of this proposed AD and the 

cost impact of AD 2003–21–07? The 

estimated cost impact of AD 2003–21–

07 on each of 116 airplanes in the U.S. 

registry is $65. This is to disengage the 

pitch trim circuit breaker and AP servo 

circuit breaker and then tie strap each 

of them to prevent them from being 

engaged. 

The estimated cost of this proposed 

AD is $3,125 or $3,255 on each of 251 

airplanes in the U.S. registry to do the 

replacement or modification of the trim 

PCB assembly. 

Compliance Time of This Proposed AD 

What would be the compliance time 

of this proposed AD? The compliance 

time of this proposed AD is within the 

next 24 calendar months after the 

effective date of this AD or within 300 

hours time-in-service (TIS) after the 

effective date of this AD, whichever 

occurs first. 

Why is the compliance time of this 

proposed AD presented in both hours 

TIS and calendar time? A single-wire 

shorting to 28 volts or a failure of a relay 

that results in the relay contacts 

remaining closed is a direct result of 

airplane operation. For example, either 

failure could occur on an affected 

airplane within a short period of 

airplane operation while you could 

operate another affected airplane for a 

considerable amount of time without 

experiencing either failure. Therefore, to 

assure that either failure is detected and 

corrected in a timely manner without 

inadvertently grounding any of the 

affected airplanes, we are using a 

compliance time based upon both hours 

TIS and calendar time. 

Regulatory Findings 

Would this proposed AD impact 

various entities? 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. 

Would this proposed AD involve a 

significant rule or regulatory action? For 

the reasons discussed above, I certify 

that this proposed AD: 

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 summary of the costs 

to comply with this proposed AD and 

placed it in the AD Docket. You may get 

a copy of this summary by sending a 

request to us at the address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

2003–CE–54–AD’’ in your request.

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 Federal Aviation Administration 

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:

5758 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2003–21–07, Amendment 39–13342 (68 

FR 60028, October 21, 2003), and by 

adding a new AD to read as follows:

The Cessna Aircraft Company: Docket No. 

2003–CE–54–AD 

When Is the Last Date I Can Submit 

Comments on This Proposed AD? 

(a) We must receive comments on this 

proposed airworthiness directive (AD) by 

April 15, 2004. 

What Other ADs Are Affected by This 

Action? 

(b) This AD supersedes AD 2003–21–07.

What Airplanes Are Affected by This AD? 

(c) This AD affects Model 525 airplanes 

with the following serial numbers that are 

certificated in any category: 

(1) Group 1 (maintains the actions from AD 

2003–21–07): 525–0001, 525–0002, and 525–

0004 through 525–0159. 

(2) Group 2: 525–0160 through 525–0359. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of Cessna having 

now developed and made changes in the 

design of the affected trim printed circuit 

board (PCB) assembly to allow the use of the 

assembly and the prevention of the singlepoint failure, and identification of additional 

airplanes that have the same unsafe 

condition. The actions specified in this AD 

are intended to correct this single-point 

failure in the electric pitch trim system, 

which will result in a runaway pitch trim 

condition where the pilot could not 

disconnect using the control wheel autopilot/

trim disconnect switch. Failure of the electric 

trim system would result in a large pitch 

mistrim and would cause excessive control 

forces that the pilot could not overcome. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following:

Actions Compliance Procedures 

(1) For Group 1 airplanes only: Disengage the 

PITCH TRIM circuit breaker located on the 

left circuit breaker panel. Install a tie strap 

(part number (P/N) MS3367–1–4 or equivalent part number) on the shaft of the PITCH 

TRIM circuit breaker from being engaged. 

Within 5 calendar days or 10 hours time-inservice after October 22, 2003 (the effective 

date of AD 2003–21–07), whichever occurs 

first. 

Not Applicable. 

(2) For Group 1 airplanes only: Disengage the 

AP SERVOS circuit breaker located in the 

right circuit breaker panel. Install a tie strap 

(P/N MS3367–1–4 or equivalent part number) 

on the shaft of the AP SERVOS circuit breaker to prevent the circuit breaker from being 

engaged. 

Within 5 calendar days or 10 hours time-inservice after October 22, 2003 (the effective 

date of AD 2003–21–07), whichever occurs 

first. 

Not Applicable. 

(3) The Minimum Crew portion of Section II—

Operating Limitations of the Airplane Flight 

Manual (AFM) provides information on applicable operating limitations with the autopilot 

inoperable. 

Not Applicable. Not Applicable. 

(4) All affected airplanes were originally 

equipped with a P/N 6518351–3 or P/N 

65138351–5 Trim PC Board Assembly. If a 

P/N 6518351–8 Trim PC Board Assembly is 

installed, contact the Wichita Aircraft Certification Office at the address in paragraph (f) 

of this AD to determine if the installed P/N 

6518351–8 Trim PC board assembly is an alternative method of compliance to this AD. 

Not Applicable. Not Applicable. 

(5) Cessna Citation Alert Service Letter 

ASL525–27–02, dated October 10, 2003, 

contains information related to this subject. 

Not Applicable. Not Applicable. 

(6) For both Group 1 and Group 2 airplanes:

Do the trim PCB assembly change as follows: (i) Modify the 6518351–8 trim PCB assembly to a 6518351–10 trim PCB assembly; 

or (ii) Replace any 6518351–3 trim PCB assembly with 6518351–10 (EX) trim PCB assembly. 

Within the next 24 calendar months after the 

effective date of this AD or within 300 hours 

time-in-service (TIS) after the effective date 

of this AD, whichever occurs first, unless already done. 

Follow the ACCOMPLISHMENT INSTRUCTIONS paragraph of Cessna Citation Service Bulletin No. SB525–27–17, dated December 9, 2003. 

(7) For both Group 1 and Group airplanes: Remove any tie strap (P/N MS3367–1–4 or 

equivalent part number) on the AP SERVOS 

and PITCH circuit breakers. (Required by AD 

2003–21–07.) 

Before further flight after the modification or 

replacement of the trim PCB assembly required by paragraph (e)(6)(i) or (e)(6)(ii) of 

this AD. 

Follow the ACCOMPLISHMENT INSTRUCTIONS paragraph of Cessna Citation Service Bulletin No. SB525–27–17, dated December 9, 2003. 

(8) For both Group 1 and Group 2 airplanes:

Do not install any 6518351–8, 6518351–3, or 

6518351–5 trim PCB assembly. 

As of the effective date of this AD. Not Applicable. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Wichita Aircraft Certification Office 

(ACO), FAA. 

(1) For information on any already 

approved alternative methods of compliance, 

contact Dan Withers, Aerospace Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Wichita, Kansas 67209; telephone: (316) 946–

4196; facsimile: (316) 946–4107. 

(2) Alternative methods of compliance 

approved for AD 2003–21–07 are not 

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5759

approved as alternative methods of 

compliance for this AD. 

May I Get Copies of the Documents 

Referenced in This AD? 

(g) You may get copies of the documents 

referenced in this AD from The Cessna 

Aircraft Company, Product Support, P.O. Box 

7706, Wichita, Kansas 67277; telephone: 

(316) 517–6000; facsimile: (316) 517–8500. 

You may view these documents at FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106.

Issued in Kansas City, Missouri, on January 

29, 2004. 

Dorenda D. Baker, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service.

[FR Doc. 04–2403 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–97–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135 and –145 

Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to 

certain Model EMB–135 and –145 series 

airplanes. This proposal would require 

modification of the pitch trim system, 

which includes replacing certain 

components of the system with new or 

serviceable components, and upgrading 

certain software to a newer version. This 

action is necessary to prevent the 

temporary loss of the pitch trim 

command, which could result in 

reduced controllability of the airplane 

and consequent injury to the flightcrew 

and passengers. This action is intended 

to address the identified unsafe 

condition.

DATES: Comments must be received by 

March 8, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

97–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9–anm–

nprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–97–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), P.O. Box 343—CEP 12.225, 

Sao Jose dos Campos—SP, Brazil. This 

information may be examined at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington.

FOR FURTHER INFORMATION CONTACT:

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2003–NM–97–AD.’’ The 

postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2003–NM–97–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

The Departmento de Aviacao Civil 

(DAC), which is the airworthiness 

authority for Brazil, notified the FAA 

that an unsafe condition may exist on 

certain EMBRAER Model EMB–135 and 

–145 series airplanes. The DAC advises 

that several operators have reported 

temporary loss of the pitch trim 

command during the climb after take-off 

caused by probable failure of various 

components of the pitch trim system. 

The pitch trim system consists of 

several components including the 

horizontal stabilizer control unit 

(HSCU), the horizontal stabilizer 

actuator (HSA), the aural warning unit 

(AWU), integrated computer (IC) units, 

engine indicating and crew alerting 

system/electronic flight information 

system (EICAS/EFIS) software, the 

control yoke pitch trim switch, and the 

data acquisition unit (DAU). Failure of 

the pitch trim system, if not corrected, 

could result in reduced controllability 

of the airplane and consequent injury to 

the flightcrew and passengers.

Explanation of Relevant Service 

Information 

EMBRAER has issued the following 

service bulletins related to the 

modification of the pitch trim system. 

• EMBRAER Service Bulletin 

145LEG–27–0002, dated February 5, 

2003 (for Model EMB–135BJ series 

airplanes); and EMBRAER Service 

Bulletin 145–27–0084, Revision 04, 

dated October 21, 2003 (for Model 

EMB–135ER, –135LR, –135KE, and 

–135KL series airplanes; and Model 

EMB–145, –145ER, –145MR, –145LR, 

–145XR, –145MP, and –145EP series 

airplanes); which describe procedures 

for replacing the HSCU with a new unit 

having improved features. EMBRAER 

Service Bulletin 145–27–0084 specifies 

that EMBRAER Service Bulletin 145–