5790 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–177–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

supersedure of an existing airworthiness 

directive (AD), applicable to certain 

Airbus Model A320 series airplanes, 

that currently requires repetitive 

inspections to detect fatigue cracking of 

the lower surface panel on the wing 

center box; and repair if necessary. That 

AD also requires modification of the 

lower surface panel on the wing center 

box, which constitutes terminating 

action for the repetitive inspections. 

This action would reduce the 

compliance times for the inspections 

required by the existing AD. The actions 

specified by the proposed AD are 

intended to prevent fatigue cracking of 

the lower surface panel on the wing 

center box, which could result in 

reduced structural integrity 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–

177–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–177–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 Industrie, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

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–177–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–177–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

On August 19, 1998, the FAA issued 

AD 98–22–05, amendment 39–10851 (63 

FR 56542, October 22, 1998), applicable 

to certain Airbus Model A320 series 

airplanes, to require repetitive 

inspections to detect fatigue cracking of 

the lower surface panel on the wing 

center box; and repair if necessary. That 

AD also requires modification of the 

lower surface panel on the wing center 

box, which constitutes terminating 

action for the repetitive inspections. 

That action was prompted by issuance 

of mandatory continuing airworthiness 

information by a foreign civil 

airworthiness authority. The 

requirements of that AD are intended to 

prevent fatigue cracking of the lower 

surface panel on the wing center box, 

which could result in reduced structural 

integrity of the airplane. 

Actions Since Issuance of Previous Rule 

Since the issuance of AD 98–22–05, 

the Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified the FAA that an unsafe 

condition may exist on certain Airbus 

Model A320 series airplanes. The DGAC 

advises that a full-scale fatigue survey 

on the Model A320 fleet revealed that 

the weight of fuel at landing and the 

average flight duration are higher than 

those defined for the analysis of fatiguerelated tasks. This has led to an 

adjustment of the fatigue mission for the 

A320 fleet, in that the DGAC has 

required compliance thresholds and 

repetitive intervals for accomplishment 

of the inspections for fatigue cracking 

shorter than those required by AD 98–

22–05. Fatigue-related cracking of the 

lower surface panel on the wing center 

box could result in reduced structural 

integrity of the airplane. 

Explanation of Relevant Service 

Information 

Airbus has issued Service Bulletin 

A320–57–1082, Revision 03, dated April 

30, 2002. The procedures specified in 

Revision 03 are essentially the same as 

those in Revision 01 of the service 

bulletin, which was referenced in the 

existing AD for accomplishment of the 

inspections and corrective action. 

However, Revision 03 has a change that 

recommends a reduction in the 

compliance thresholds and repetitive 

intervals specified in Revision 01. 

Airbus also has issued Service 

Bulletin A320–57–1043, Revision 05, 

dated April 30, 2002. The procedures in 

Revision 05 are essentially the same as 

those in Revision 02 of the service 

bulletin, which was referenced in the 

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5791

existing AD for accomplishment of the 

modification. Revision 05 recommends 

a reduction in the compliance 

thresholds specified in Revision 03, and 

contains editorial changes. 

The DGAC classified these service 

bulletins as mandatory and issued 

French airworthiness directive 2002–

342(B), dated June 26, 2002, to ensure 

the continued airworthiness of these 

airplanes in France. 

FAA’s Conclusions 

This airplane model is manufactured 

in France 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 us informed of the 

situation described above. We have 

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 AD 

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 

supersede AD 98–22–05 to continue to 

require repetitive inspections to detect 

fatigue cracking of the lower surface 

panel on the wing center box; and repair 

if necessary. The proposed AD also 

would continue to require modification 

of the lower surface panel on the wing 

center box, which constitutes 

terminating action for the repetitive 

inspections. This new action would 

reduce both the threshold and repetitive 

intervals for the inspections for fatigue 

cracking of the same area. The actions 

would be required to be accomplished 

in accordance with the service bulletins 

described previously, except as 

discussed below. 

Differences Between Proposed AD and 

Service Information 

Although Airbus Service Bulletin 

A320–57–1082, Revision 03, specifies 

that the manufacturer may be contacted 

for disposition of certain repair 

conditions, this proposed AD would 

require the repair of those conditions to 

be accomplished in accordance with a 

method approved by either us or the 

DGAC (or its delegated agent). In light 

of the type of repair that would be 

required to address the identified unsafe 

condition, and in consonance with 

existing bilateral airworthiness 

agreements, we have determined that a 

repair approved by either us or the 

DGAC (or its delegated agent) would be 

acceptable for compliance with this 

proposed AD.

Unlike the procedures described in 

Service Bulletin A320–57–1082, this 

proposed AD would not permit further 

flight if fatigue cracks are detected on 

the lower surface panel of the wing 

center box. We have determined that, 

because of the safety implications and 

consequences associated with such 

fatigue cracking, any subject lower 

surface panel that is found to be cracked 

must be repaired prior to further flight 

in accordance with a method approved 

by either us or the DGAC (or its 

delegated agent). 

Service Bulletin A320–57–1082 

describes procedures for completing and 

submitting a sheet recording compliance 

with the service bulletin. This proposed 

AD would not require those actions; we 

do not need this information from 

operators. 

Work Hour Rate Increase 

We have reviewed the figures we have 

used over the past several years to 

calculate AD costs to operators. To 

account for various inflationary costs in 

the airline industry, we find it necessary 

to increase the labor rate used in these 

calculations from $60 per work hour to 

$65 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly labor 

rate. 

Cost Impact 

There are approximately 60 airplanes 

of U.S. registry that would be affected 

by this proposed AD. This proposed AD 

would reduce the compliance time for 

the inspections required by AD 98–22–

05, and consequently adds no additional 

costs or work. The current costs 

associated with that AD are repeated as 

follows for the convenience of affected 

operators: 

The inspections that are currently 

required by AD 98–22–05, and retained 

in this proposed AD, take approximately 

2 work hours per airplane to 

accomplish, at an average labor rate of 

$65 per work hour. Based on these 

figures, the cost impact of the currently 

required inspections is estimated to be 

$130 per airplane, per inspection cycle. 

The modification that is currently 

required by AD 98–22–05, and retained 

in this proposed AD, would take 

approximately 2 work hours per 

airplane to accomplish, at an average 

labor rate of $65 per work hours. There 

are no parts necessary to accomplish the 

modification. Based on these figures, the 

cost impact of the modification 

currently required is estimated to be 

$130 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.

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.