5778 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

airplane per AFM Supplement 8, or 

accomplishment of the repetitive flight 

checks per paragraph (c) of this AD, is no 

longer required. Then, at the time specified 

in paragraph (d)(1) or (d)(2) of this AD, as 

applicable, repeat the actions required by 

paragraph (b) or (c) of this AD. 

(1) For propeller blades that have not been 

overhauled: Prior to the accumulation of 

6,000 total flight hours on any propeller 

blade. 

(2) For overhauled propeller blades: Within 

7 days after overhauling any propeller blade. 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, is 

authorized to approve alternative methods of 

compliance for this AD.

Note 1: The subject of this AD is addressed 

in British airworthiness directive 001–11–

2001.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2474 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–18–AD] 

RIN 2120–AA64

Airworthiness Directives; Saab Model 

SAAB SF340A and SAAB 340B 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 Saab Model SAAB SF340A and 

Model SAAB 340B series airplanes. This 

proposal would require inspections of 

the internal structure of the nacelles for 

cracks, deformations, or other damage, 

and corrective actions if necessary. This 

action is necessary to prevent fatigue 

cracks in the outer flange of the nacelle 

frame, which could result in reduced 

structural integrity of the nacelle 

supporting structure. 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–

18–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. 2003–NM–18–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 for 

Windows or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Saab Aircraft AB, SAAB Aircraft 

Product Support, S–581.88, Linko ̈ping, 

Sweden. 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 2003–NM–18–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–18–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

The Luftfartsverket (LFV), which is 

the airworthiness authority for Sweden, 

notified the FAA that an unsafe 

condition may exist on certain Saab 

Model SAAB SF340A and SAAB 340B 

series airplanes. The LFV advises that it 

has received reports of fatigue cracks in 

the outer flange of nacelle frame station 

203 between water line (WL) 92 to 

WL96. This condition, if not detected 

and corrected in a timely manner, could 

lead to reduced structural integrity of 

the nacelle supporting structure. 

Explanation of Relevant Service 

Information 

Saab has issued Service Bulletin 340–

54–043, dated December 18, 2002, 

which describes procedures for detailed 

and ultrasonic inspections of the 

internal structure of the nacelles for 

cracks, deformations and damage, and 

corrective actions if necessary. The 

corrective actions include replacement 

of the firedeck attachment angle with a 

new angle and repair of cracks, 

deformation, and damage. This service 

bulletin recommends compliance times 

for the inspections at the following 

approximate flight cycle levels: 

1. For airplanes with less than 20,000 

total flight cycles, accomplish before 

24,000 total flight cycles; and 

2. For airplanes with 20,000 total 

flight cycles or more, accomplish within 

2,000 to 4,000 flight cycles after the 

service bulletin’s release date, 

depending on the airplane’s total flight 

cycles. 

Accomplishment of the actions 

specified in the service bulletin is 

intended to adequately address the 

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5779

identified unsafe condition. The LFV 

classified this service bulletin as 

mandatory and issued Swedish 

airworthiness directive No 1–176, dated 

December 20, 2002, in order to assure 

the continued airworthiness of these 

airplanes in Sweden. 

FAA’s Conclusions 

These airplane models are 

manufactured in Sweden 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, the LFV has 

kept the FAA informed of the situation 

described above. The FAA has 

examined the findings of the LFV, 

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 bulletin described 

previously, except as discussed below.

Differences Between Proposed Rule and 

Service Bulletin 

Although the service bulletin 

specifies that operators may contact the 

manufacturer for disposition of certain 

repairs, this proposal would require 

operators to repair per a method 

approved by either the FAA or LFV (or 

its delegated agent). In light of the type 

of repair 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 repair approved by either the FAA or 

LFV would be acceptable for 

compliance with this proposed AD. 

Clarification of Compliance Times 

For compliance times, the service 

bulletin specifies ‘‘accumulated flights’’

and ‘‘flights’’. However, for these 

compliance times, paragraph (c) of this 

proposed AD specifies ‘‘total flight 

cycles’’ and ‘‘flight cycles’’. This 

decision is based on our determination 

that ‘‘accumulated flights’’ and ‘‘flights’’

may be interpreted differently by 

different operators. We find that our 

proposed terminology is generally 

understood within the industry and 

records will always exist that establish 

these cycles with certainty. 

Cost Impact 

The FAA estimates that 224 airplanes 

of U.S. registry would be affected by this 

proposed AD, that it would take 

approximately 4 work hours per 

airplane to accomplish the proposed 

inspection, and that the average labor 

rate is $65 per work hour. Based on 

these figures, the cost impact of the 

proposed AD on U.S. operators is 

estimated to be $58,240, or $260 per 

airplane. 

The cost impact figure discussed 

above is 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 proposed 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:

Saab Aircraft AB: Docket 2003–NM–18–AD.

Applicability: Model SAAB SF340A series 

airplanes with serial numbers 004 through 

159 inclusive, and Model SAAB 340B series 

airplanes with serial numbers 160 through 

459 inclusive, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent fatigue cracks in the outer 

flange of the nacelle frame, which could 

result in reduced structural integrity of the 

nacelle supporting structure, accomplish the 

following: 

Inspection 

(a) Perform detailed and ultrasonic 

inspections, as applicable, of the internal 

structure of the nacelles for cracks, 

deformations, or other damage, in accordance 

with the Accomplishment Instructions of 

Saab Service Bulletin 340–54–043, dated 

December 18, 2002. Do the inspection at the 

applicable time specified by paragraph 1.D, 

‘‘Compliance’’, of the service bulletin, except 

as required by paragraph (b) and (c) of this 

AD.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

(b) Where the service bulletin specified in 

paragraph (a) of this AD specifies a 

compliance time relative to the release date 

of the service bulletin, this AD requires 

compliance following the effective date of 

this AD. 

(c) Where the service bulletin specified in 

paragraph (a) of this AD uses ‘‘accumulated 

flights’’ and ‘‘flights’’ for compliance times, 

this AD requires operators to use ‘‘total flight 

cycles’’ and ‘‘flight cycles’’. 

Repair 

(d) If any crack, deformation, or damage is 

found during any inspection required by 

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

repair and replace the firedeck attachment 

angle with a new angle, as applicable, in 

accordance with the Accomplishment 

Instructions of Saab Service Bulletin 340–54–

5780 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

043, dated December 18, 2002. Where the 

service bulletin specifies contacting the 

manufacturer for disposition of repairs, 

before further flight, repair per a method 

approved by the Manager, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate; or the Luftfartsvarket (or its 

delegated agent). 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, 

FAA, is authorized to approve alternative 

methods of compliance with this AD.

Note 2: The subject of this AD is addressed 

in Swedish airworthiness directive No 1–176, 

dated December 20, 2002.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2475 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–160–AD] 

RIN 2120–AA64 

Airworthiness Directives; 

Construcciones Aeronauticas, S.A. 

(CASA), Model C–235 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 CASA Model C–235 series 

airplanes. This proposal would require 

modification of the electrical wiring of 

the rudder trim control unit. This action 

is necessary to prevent the flight crew 

from being able to inhibit the aural 

warning for the landing gear up. If the 

flight crew of the next flight or possibly 

of the same flight is unaware that the 

aural warning had been disabled, they 

could inadvertently land the airplane 

with the landing gear not down and 

locked. 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–

160–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–160–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–160–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–160–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 Construcciones 

Aeronauticas, S.A. (CASA), Model C–

235 series airplanes. The DGAC advises 

that an operator did not have an aural 

warning that the landing gear was in the 

‘‘up’’ position when the airplane was in 

a landing configuration (wing flaps 

extended) as required by paragraph 

(e)(4) of Section 25.729 (‘‘Retracting 

Mechanism’’) of the Federal Aviation 

Regulations (FAR) (14 CFR 25.729). 

Investigation revealed that the operator 

had inhibited the aural warning during 

the previous approach for landing. If the 

flight crew is able to inhibit the aural 

warning for the landing gear up, the 

flight crew of the next flight or possibly 

of the same flight could be unaware that 

the aural warning had been disabled 

and could inadvertently land the 

airplane with the landing gear not down 

and locked.

Explanation of Relevant Service 

Information 

CASA has issued Service Bulletin SB–

235–27–20, dated March 7, 2001, which 

describes procedures for modification of 

the electrical wiring of the rudder trim 

control unit. Accomplishment of the 

actions specified in the service bulletin 

is intended to adequately address the 

identified unsafe condition. The DGAC 

classified this service bulletin as 

mandatory and issued Spanish 

airworthiness directive 02/02, dated 

April 30, 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