5762 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

2003 (for Model EMB–135BJ series 

airplanes); or paragraph 3.J. (Part I) of 

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); as 

applicable. 

(2) For airplanes listed in EMBRAER 

Service Bulletin 145–27–0091, Change 02, 

dated November 27, 2002: Replace the 

horizontal stabilizer actuator (HSA) with a 

new HSA having a new part number in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

(3) For airplanes listed in EMBRAER 

Service Bulletin 145–31–0028, Change 04, 

dated December 20, 2002: Replace the aural 

warning unit (AWU) with an AWU having 

improved features and a new part number in 

accordance with the Accomplishment 

Instructions of the service bulletin.

Note 1: EMBRAER Service Bulletin 145–

31–0028 references Grimes Aerospace 

Company Service Bulletin 80–0694–33–

SB01, dated January 1, 2002, as an additional 

source of service information for 

accomplishment of the replacement. The 

Grimes Aerospace service bulletin is 

included in the EMBRAER service bulletin.

(4) For airplanes listed in EMBRAER 

Service Bulletin 145LEG–31–0001, dated 

August 19, 2002 (for Model EMB–135BJ 

series airplanes); or EMBRAER Service 

Bulletin 145–31–0033, Revision 03, dated 

August 25, 2003 (for Model EMB–135ER, 

–135LR, –135KE, and –135KL series 

airplanes; and Model EMB–145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP series airplanes): Replace any IC–600 

units having part numbers (P/N) 7107000–

82407, –82407 MODS–B, –82427, –83407, 

and –83407 MODS–B, with new IC–600 MOD 

AB units having P/Ns 7107000–82428, or 

–83428, as applicable; and install a new 

software version 18.5 (phase 8.5) of the 

EICAS/EFIS system for all IC–600 MOD AB 

hardware. Accomplish the actions in 

accordance with the Accomplishment 

Instructions of the applicable service 

bulletin.

Note 2: EMBRAER Service Bulletins 

145LEG–31–0001 and 145–31–0033 reference 

Honeywell Service Bulletin 7017000–22–

6089, Revision 003, dated October 16, 2003, 

as an additional source of service information 

for accomplishment of the replacement and 

installation.

(5) For airplanes listed in EMBRAER 

Service Bulletin 145LEG–27–0004, dated 

January 21, 2003 (for Model EMB–135BJ 

series airplanes); or EMBRAER Service 

Bulletin 145–27–0096, Revision 03, dated 

September 2, 2003 (for Model EMB–135ER, 

–135LR, –135KE, and –135KL series 

airplanes, and Model EMB–145, –145ER, 

–145MR, –145LR, –145XR, –145MP, and 

–145EP series airplanes): Replace the control 

yoke pitch trim switch with a new switch 

having a new part number; and replace the 

placard around the switch knob, as 

applicable, with a new placard having a new 

part number in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin. 

(6) For airplanes listed in EMBRAER 

Service Bulletin 145–27–0073, Change 02, 

dated February 26, 2002: Replace the pitch 

trim back-up control switch with a new 

switch having a new part number (including 

reidentifying the trim control panel) in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

(7) For all airplanes: Connect the HSCU 

and the data acquisition unit (DAU) 

(including the replacement of the pitch trim 

system circuit breakers with new circuit 

breakers sized for the new system load 

capacity, as applicable) in accordance with 

paragraph 3.K. (Part II) of EMBRAER Service 

Bulletin 145LEG–27–0002, dated February 5, 

2003 (for Model EMB–135BJ series 

airplanes); or paragraphs 3.K., 3.L., 3.M., and 

3.N. (Parts II, III, IV, and V) of 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). 

Parts Installation 

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

person may install, on any airplane, a part 

unless it has been modified in accordance 

with the applicable paragraph of the affected 

service bulletins listed in Table 1 of this AD.

TABLE 1.—PARTS INSTALLATION

PARAGRAPHS

EMBRAER service bulletin 

Parts

installation 

paragraph 

145–27–0084, Revision 04, 

dated October 21, 2003.

1.C.(1)(a) 

145LEG–27–0002, dated 

February 5, 2003.

1.C.(1)(a) 

145–27–0091, Change 02, 

dated November 27, 2002.

1.C.(1)(a) 

145–31–0028, Change 04, 

dated December 20, 2002.

1.C.(a) 

145–31–0033, Revision 03, 

dated August 25, 2003.

1.C.(1) 

Actions Accomplished Per Previous Issues of 

Service Bulletins 

(d) Actions accomplished before the 

effective date of this AD in accordance with 

the service bulletins listed in Table 2 of this 

AD are considered acceptable for compliance 

with the corresponding action specified in 

this AD.

TABLE 2.—PREVIOUS ISSUES OF

SERVICE BULLETINS

EMBRAER 

service

bulletin 

Revision and date 

145–31–0028 Original Issue, December 13, 

2001. 

Revision 01, January 22, 

2002. 

Revision 02, April 2, 2002. 

Revision 03, August 22, 2002. 

145–31–0033 Revision 02, April 27, 2003. 

Revision 03, August 25, 2003. 

TABLE 2.—PREVIOUS ISSUES OF

SERVICE BULLETINS—Continued

EMBRAER 

service

bulletin 

Revision and date 

145–27–0083 Original Issue, October 4, 

2001. 

Revision 01, March 15, 2002. 

Revision 02, April 11, 2002. 

Revision 03, July 16, 2002. 

145–27–0084 Revision 01, December 20, 

2002. 

Revision 02, February 25, 

2003. 

Revision 03, July 15, 2003. 

145–27–0096 Revision 01, April 7, 2003. 

Revision 02, July 1, 2003. 

Revision 03, September 2, 

2003. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD.

Note 3: The subject of this AD is addressed 

in Brazilian airworthiness directive 2003–03–

01, dated April 3, 2003.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2467 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–262–AD] 

RIN 2120–AA64 

Airworthiness Directives; 

Construcciones Aeronauticas, S.A. 

(CASA), Model C–212 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 all 

CASA Model C–212 series airplanes. 

This proposal would require rework of 

the nose landing gear (NLG); 

modification of the hydraulic steering 

system; a test of the cable tension for the 

nosewheel steering system when 

abnormal vibration occurs, and 

adjustment of the cable tension, if 

necessary; and a revision to the 

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5763

Limitations section of the airplane flight 

manual to include certain procedures to 

be performed during the takeoff run. 

This action is necessary to prevent 

failure of the auxiliary landing gear 

direction system, which could result in 

abnormal vibrations during takeoff and 

landing runs, and consequent reduced 

controllability of the airplane. 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. 2002–NM–

262–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-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2002–NM–262–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 

Construcciones Aeronauticas, S.A., 

Getafe, Madrid, Spain. This information 

may be examined at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

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

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 2002–NM–262–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. 

2002–NM–262–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

The Direccio ́n General de Aviacio ́n 

Civil (DGAC), which is the 

airworthiness authority for Spain, 

notified the FAA that an unsafe 

condition may exist on all CASA Model 

C–212 series airplanes. The DGAC 

advises that failures of the auxiliary 

landing gear direction system have been 

reported, which produced abnormal 

vibrations during takeoff and landing 

runs. The failure was caused by a 

gradual loss of hydraulic oil pressure in 

the selector direction valve, and by a 

loss of tension in the cable for the 

nosewheel steering system. This 

condition, if not corrected, could result 

in the failure of the auxiliary landing 

gear direction system, which could 

cause abnormal vibrations during 

takeoff and landing runs, and 

consequent reduced controllability of 

the airplane. 

Explanation of Relevant Service 

Information 

CASA has issued CASA Service 

Bulletin 212–32–21, Revision 2, dated 

November 10, 1987, which describes 

procedures for reworking the nose 

landing gear (NLG). The rework of the 

NLG includes replacing bushings and 

washers with new parts, if necessary; 

installing a new helicoil; re-identifying 

and re-installing the lower attachment 

fitting; installing a new lockwasher and 

nut; installing a new nut on the shock 

absorber assembly; removing any gear 

crown assembly that has broken teeth, 

dirt, corrosion, or uneven wear, and 

replacing it with a new or serviceable 

gear crown assembly; re-identifying and 

re-installing the ring nut of the shock 

absorber assembly; and installing a new 

actuator. 

CASA has also issued EADS CASA 

Service Bulletin SB–212–32–22, 

Revision 2, dated July 28, 1997, which 

describes procedures for modifying the 

hydraulic steering system of the NLG. 

The modification of hydraulic steering 

system involves modifying the 

hydraulic installation and the nose 

fuselage; modifying the electrical 

installation and the center instrument 

panel, as applicable; and modifying the 

electrical system and overhead panel, as 

applicable. This service bulletin also 

contains procedures for testing the cable 

tension of the nosewheel steering 

system, and adjusting the tension, if 

necessary. 

CASA has also issued EADS CASA 

COM 212–172, Revision 04, dated 

December 9, 2002; and CASA COM 

212–173, Revision 3, dated February 22, 

1995. These communications contain 

information and procedures related to 

maintenance, troubleshooting, overhaul, 

tests, and tolerances for landing gear 

units of the affected airplanes. The 

information in these documents has 

been consolidated from several different 

documents including service bulletins, 

maintenance manuals, technical orders, 

and the structural repair manual.

Accomplishment of the actions 

specified in the service bulletins and the 

COMs is intended to adequately address 

the identified unsafe condition. The 

DGAC classified these service bulletins 

and COMs as mandatory and issued 

Spanish airworthiness directive 01/02, 

dated April 17, 2002, to ensure the 

continued airworthiness of these 

airplanes in Spain. 

FAA’s Conclusions 

This airplane model is manufactured 

in Spain and is 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, 

the DGAC has kept the FAA informed 

of the situation described above. The 

5764 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

FAA has examined the findings of the 

DGAC, reviewed all available 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

Explanation of Requirements of 

Proposed Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other airplanes of the same 

type design registered in the United 

States, the proposed AD would require 

accomplishment of the actions specified 

in the service bulletins described 

previously, except as discussed below. 

The proposed AD would also require 

revising the Limitations section of the 

airplane flight manual to include certain 

procedures to be performed during the 

takeoff run. 

Cost Impact 

The FAA estimates that 27 airplanes 

of U.S. registry would be affected by this 

proposed AD, that it would take 

approximately 6 work hours per 

airplane to accomplish the proposed 

rework of the NLG; and that the average 

labor rate is $65 per work hour. Based 

on these figures, the cost impact of this 

proposed action on U.S. operators is 

estimated to be $10,530, or $390 per 

airplane. 

We estimate that it would take 

approximately 92 work hours per 

airplane to accomplish the proposed 

modification of the hydraulic steering 

system. Based on these figures, the cost 

impact of this proposed action on U.S. 

operators is estimated to be $161,460, or 

$5,980 per airplane. 

We estimate that it would take 

approximately 1 work hour per airplane 

to revise the Limitations section of the 

airplane flight manual. Based on these 

figures, the cost impact of this proposed 

action on U.S. operators is estimated to 

be $1,755, or $65 per airplane. 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the proposed requirements of this AD 

action, and that no operator would 

accomplish those actions in the future if 

this AD were not adopted. The cost 

impact figures discussed in AD 

rulemaking actions represent only the 

time necessary to perform the specific 

actions actually required by the AD. 

These figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations proposed herein 

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. Therefore, 

it is determined that this proposal 

would not have federalism implications 

under Executive Order 13132. 

For the reasons discussed above, I 

certify that this 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) if 

promulgated, 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. A copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(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. Section 39.13 is amended by 

adding the following new airworthiness 

directive:

Construcciones Aeronauticas, S.A. (CASA):

Docket 2002–NM–262–AD.

Applicability: All Model C–212 series 

airplanes, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the auxiliary landing 

gear direction system, which could result in 

abnormal vibrations during takeoff and 

landing runs, and consequent reduced 

controllability of the airplane, accomplish 

the following: 

Rework and Modification 

(a) Within 6 months after the effective date 

of this AD, accomplish the actions in 

paragraphs (a)(1) and (a)(2) of this AD in 

accordance with the applicable service 

bulletin. 

(1) Rework the nose landing gear (NLG) in 

accordance with the Accomplishment 

Instructions of CASA Service Bulletin 

SB212–32–21, Revision 2, dated November 

10, 1987. 

(2) Modify the hydraulic steering system of 

the NLG in accordance with the Instructions 

for Accomplishment of EADS CASA Service 

Bulletin SB–212–32–22, Revision 2, dated 

July 28, 1997. 

Tension Test and Adjustment 

(b) Within 600 flight hours after any 

abnormal vibration of the nosewheel steering 

system occurs, test the cable tension of the 

nosewheel steering system. Adjust the 

tension, if necessary. Accomplish these 

actions in accordance with EADS CASA 

COM 212–172, Revision 04, dated December 

9, 2002; or CASA COM 212–173, Revision 3, 

dated February 22, 1995; as applicable. 

Airplane Flight Manual Revision 

(c) Within 6 months after the effective date 

of this AD, revise the Limitations Section of 

the FAA-approved Airplane Flight Manual 

(AFM) to include the following statement. 

This may be accomplished by inserting a 

copy of this AD in the AFM.

‘‘Nose wheel malfunction during take-off 

run—Initiate or ‘‘perform’’ normal RTO 

procedures.’’

Note 1: When a statement identical to that 

in paragraph (c) of this AD has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM.

Parts Installation 

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

person may install on any airplane an NLG 

unless it has been reworked in accordance 

with paragraph (a)(1) of this AD. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, is 

authorized to approve alternative methods of 

compliance for this AD.

Note 2: The subject of this AD is addressed 

in Spanish airworthiness directive 01/02, 

dated April 17, 2002.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2468 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P