5792 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

§ 39.13 [Amended] 

2. Section 39.13 is amended by 

removing amendment AD 39–10851 (63 

FR 56542, October 22, 1998), and by 

adding a new airworthiness directive 

(AD), to read as follows:

Airbus: Docket 2002–NM–177–AD. 

Supersedes AD 98–22–05, Amendment 

39–10851.

Applicability: Model A320 series airplanes, 

certificated in any category, on which Airbus 

Modification 22418 (reference Airbus Service 

Bulletin A320–57–1043) has not been done. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent fatigue cracking of the lower 

surface panel on the wing center box, which 

could result in reduced structural integrity of 

the airplane, accomplish the following: 

Restatement of Requirements of AD 98–22–

05 

Repetitive Inspections 

(a) Except as provided by paragraph (e) of 

this AD: Prior to the accumulation of 20,000 

total flight cycles, or within 60 days after 

November 27, 1998 (the effective date of AD 

98–22–05, amendment 39–10851), whichever 

occurs later, perform a high frequency eddy 

current inspection to detect fatigue cracking 

of the lower surface panel on the wing center 

box, in accordance with Airbus Service 

Bulletin A320–57–1082, Revision 01, dated 

December 10, 1997, or Revision 03, dated 

April 30, 2002. Repeat the eddy current 

inspection thereafter at intervals not to 

exceed 7,500 flight cycles until the actions 

required by paragraph (c) of this AD are 

accomplished. 

Repair 

(b) Except as provided by paragraph (d) of 

this AD: If any cracking is detected during 

any inspection required by paragraph (a) of 

this AD, prior to further flight, repair in 

accordance with Airbus Service Bulletin 

A320–57–1082, Revision 01, dated December 

10, 1997, or Revision 03, dated April 30, 

2002. Accomplishment of the repair 

constitutes terminating action for the 

repetitive inspections for the repaired area 

only. 

Inspection/Modification/Repair 

(c) Prior to the accumulation of 25,000 total 

flight cycles, or within 60 days after 

November 27, 1998, whichever occurs later: 

Perform a high frequency eddy current 

inspection to detect fatigue cracking of the 

lower surface panel on the wing center box, 

in accordance with Airbus Service Bulletin 

A320–57–1082, Revision 01, dated December 

10, 1997, or Revision 03, dated April 30, 

2002. 

(1) If no cracking is detected: Prior to 

further flight, modify the lower surface panel 

on the wing center box, in accordance with 

Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997, or Revision 

05, dated April 30, 2002. Accomplishment of 

the modification constitutes terminating 

action for the requirements of paragraph (a) 

of this AD. 

(2) Except as provided by paragraph (d) of 

this AD, if any cracking is detected: Prior to 

further flight, repair in accordance with 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997, or 

Revision 03, dated April 30, 2002; and 

modify any uncracked area in accordance 

with Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997, or Revision 

05, dated April 30, 2002. Accomplishment of 

the repair of cracked area(s) and modification 

of uncracked area(s) constitutes terminating 

action for the requirements of paragraph (a) 

of this AD. 

(d) If any cracking is detected during any 

inspection required by paragraph (b) or (c)(2) 

of this AD, and the applicable service 

bulletin specifies to contact Airbus for an 

appropriate action: Prior to further flight, 

repair in accordance with a method approved 

by either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (or its delegated agent). 

(e) The actions required by paragraph (a) of 

this AD are not required to be accomplished 

if the requirements of paragraph (c) of this 

AD are accomplished at the time specified in 

paragraph (a) of this AD. 

New Requirements of This AD 

Initial Inspection 

(f) For airplanes on which the inspection 

required by paragraph (a) of this AD has not 

been done before the effective date of this 

AD: Perform a high frequency eddy current 

inspection to detect fatigue cracking of the 

lower surface panel on the wing center box, 

in accordance with Airbus Service Bulletin 

A320–57–1082, Revision 01, dated December 

10, 1997; or Revision 03, dated April 30, 

2002; at the later of the times specified in 

paragraphs (f)(1) and (f)(2) of this AD. 

Accomplishment of the inspections required 

by this paragraph terminates the 

requirements of paragraph (a) of this AD. 

(1) Prior to the accumulation of 13,200 

total flight cycles or 39,700 total flight hours, 

whichever is first. 

(2) Prior to the accumulation of 20,000 

total flight cycles, or within 3,500 flight 

cycles after the effective date of this AD, 

whichever is first. 

Repetitive Inspections 

(g) If no cracking is detected during the 

inspection required by paragraph (a) or (f) of 

this AD: Repeat the inspection at the 

applicable time specified in paragraph (g)(1) 

or (g)(2) of this AD. 

(1) For airplanes on which the inspections 

required by paragraph (a) of this AD have 

been done before the effective date of this 

AD: Do the next inspection within 5,700 

flight cycles after accomplishment of the last 

inspection, or within 1,800 flight cycles after 

the effective date of this AD, whichever is 

later. Repeat the inspection thereafter at 

intervals not to exceed 5,700 flight cycles. 

(2) For airplanes on which no inspection 

required by paragraph (a) of this AD has been 

done before the effective date of this AD: Do 

the next inspection within 5,700 flight cycles 

after accomplishment of the inspection 

required by paragraph (f) of this AD. Repeat 

the inspection thereafter at intervals not to 

exceed 5,700 flight cycles. 

Repair/Modification 

(h) If any cracking is detected during any 

inspection required by paragraph (f) or (g) of 

this AD, prior to further flight, repair in 

accordance with Airbus Service Bulletin 

A320–57–1082, Revision 01, dated December 

10, 1997; or Revision 03, dated April 30, 

2002; and modify any uncracked area in 

accordance with Airbus Service Bulletin 

A320–57–1043, Revision 02, dated May 14, 

1997; or Revision 05, dated April 30, 2002. 

Where Service Bulletin A320–57–1082 

specifies to contact Airbus for an appropriate 

repair action: Prior to further flight, repair in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) (or its delegated 

agent). Accomplishment of the repair of 

cracked area(s) and modification of 

uncracked area(s) constitutes terminating 

action for the requirements of this AD. 

Actions Done per Previous Issues of Service 

Bulletins 

(i) Accomplishment of inspections and 

repairs before the effective date of this AD in 

accordance with Airbus Service Bulletin 

A320–57–1082, Revision 02, dated July 26, 

1999; and accomplishment of the 

modification before the effective date of this 

AD in accordance with Airbus Service 

Bulletin Airbus Service Bulletin A320–57–

1043, dated February 16, 1993; Revision 01, 

dated June 14, 1996; Revision 03, dated 

October 24, 1997; or Revision 04, dated 

March 15, 1999; are considered acceptable 

for compliance with the applicable actions 

specified in this AD. 

Alternative Methods of Compliance 

(j) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, is 

authorized to approve alternative methods of 

compliance for this AD.

Note 1: The subject of this AD is addressed 

in French airworthiness directive 2002–

342(B), dated June 26, 2002.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2481 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–25–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab Model 

SAAB SF340A and SAAB 340B Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5793

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 

SAAB 340B series airplanes. This 

proposal would require replacement of 

certain assistor springs and bearings 

with certain new assistor springs and 

bearings. This action is necessary to 

prevent possible collapse of a main 

landing gear upon landing 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. 2003–NM–

25–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–25–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 

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:

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–25–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–25–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

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. LFV advises that 

certain assistor springs of the main 

landing gear with the wire-formed end 

loop design have failed in service. 

Further, one known incident has been 

reported where the assistor spring cable 

(wire-rope) prevented the main landing 

gear from locking in fully down 

position. Such assistor spring failure, if 

not corrected, could result in collapse of 

a main landing gear upon landing and 

consequent reduced controllability of 

the airplane. 

Explanation of Relevant Service 

Information 

Saab has issued Service Bulletin 340–

32–130, dated April 28, 2003, which 

describes procedures for replacement of 

assistor springs and bearings of the main 

landing gear with new assistor springs 

and bearings, respectively. 

Accomplishment of the actions 

specified in the service bulletin is 

intended to adequately address the 

identified unsafe condition. LFV 

classified this service bulletin as 

mandatory and issued Swedish 

airworthiness directive No 1–191, dated 

April 28, 2003 to ensure the continued 

airworthiness of these airplanes in 

Sweden. 

LFV refers to Saab Service Bulletin 

340–32–126, dated December 18, 2002, 

as a factor in determining the 

appropriate compliance time for 

accomplishment of the actions required 

by this AD. 

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, LFV has kept 

the FAA informed of the situation 

described above. The FAA has 

examined the findings of 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. 

Cost Impact 

The FAA estimates that 288 airplanes 

of U.S. registry would be affected by this 

proposed AD, that it would take 

approximately 2 work hours per 

airplane to accomplish the proposed 

actions, and that the average labor rate 

is $65 per work hour. Required parts 

would cost approximately $750 per 

airplane. Based on these figures, the cost 

impact of the proposed AD on U.S. 

operators is estimated to be $253,440, or 

$880 per airplane.

5794 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

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 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–25–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 possible collapse of a main 

landing gear upon landing and consequent 

reduced controllability of the airplane, 

accomplish the following: 

Replacements 

(a) Within the Compliance Times listed in 

Table 1 of this AD, perform the actions 

specified in paragraphs (a)(1) and (a)(2) of 

this AD per the Accomplishment Instructions 

of Saab Service Bulletin (SB) 340–32–130, 

dated April 28, 2003.

TABLE 1.—COMPLIANCE TIMES

Within— If—

6 months after the effective date of this AD ............................................ Saab SB 340–32–126, dated December 18, 2002 has been performed. 

3 months after the effective date of this AD ............................................ Saab SB 340–32–126, dated December 18, 2002 has not been performed. 

(1) Replace the assistor springs of the main 

landing gear with new assistor springs, per 

Part 1 of the service bulletin. 

(2) Replace the bearings of the main 

landing gear with new bearings, per Part 2 of 

the service bulletin. 

Parts Installation 

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

person may install an assistor spring, part 

number AIR125132 or AIR131330, on any 

airplane. 

Alternative Methods of Compliance 

(c) 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 1: The subject of this AD is addressed 

in Swedish airworthiness directive No 1–191, 

dated April 28, 2003.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2482 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–278–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319 and A320 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 Airbus Model A319 and A320 

series airplanes. This proposal would 

require modifying the electrical bonding 

of the fuel return line in each wing 

between ribs 7 and 8. This action is 

necessary to reduce the potential for 

electrical arcing within the fuel tank 

due to insufficient electrical bonding, 

which could result in a fire or explosion 

in the fuel tank. 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–

278–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–278–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 

Airbus, 1 Rond Point Maurice Bellonte,