41398 Federal Register / Vol. 69, No. 131 / Friday, July 9, 2004 / Rules and Regulations 

Parts Installation 

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

person may install, on any airplane, a POB 

with a part number and serial number listed 

in Airbus Service Bulletin A310–27–2096, 

Revision 01, dated September 19, 2001. 

No Reporting or Return of Parts Is Required 

(e) Although the service bulletins 

referenced in this AD specify to submit 

certain information and return POBs with 

affected serial numbers to the POB 

manufacturer, this AD does not include such 

a requirement. 

Alternative Methods of Compliance 

(f) 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. 

Incorporation by Reference 

(g) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Airbus Service Bulletin A310–27–2096, 

Revision 01, dated September 19, 2001. This 

incorporation by reference was approved by 

the Director of the Federal Register in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Copies may be obtained from Airbus, 

1 Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

Note 2: The subject of this AD is addressed 

in French airworthiness directive 2001–

185(B), dated May 16, 2001.

Effective Date 

(h) This amendment becomes effective on 

August 13, 2004.

Issued in Renton, Washington, on June 24, 

2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–15370 Filed 7–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–177–AD; Amendment 

39–13718; AD 2004–14–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320–111, –211, –212, and –231 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Airbus Model 

A320–111, –211, –212, and –231 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 amendment 

reduces the compliance times for the 

inspections required by the existing AD. 

The actions specified by this 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: Effective August 13, 2004. 

The incorporation by reference of 

Airbus Service Bulletin A320–57–1082, 

Revision 03, dated April 30, 2002; and 

Airbus Service Bulletin A320–57–1043, 

Revision 05, dated April 30, 2002; as 

listed in the regulations; is approved by 

the Director of the Federal Register as of 

August 13, 2004. 

The incorporation by reference of 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997; 

and Airbus Service Bulletin A320–57–

1043, Revision 02, dated May 14, 1997; 

as listed in the regulations; was 

approved previously by the Director of 

the Federal Register as of November 27, 

1998 (63 FR 56542, October 22, 1998).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

This information may be examined at 

the Federal Aviation Administration 

(FAA), Transport Airplane Directorate, 

Rules Docket, 1601 Lind Avenue, SW., 

Renton, Washington; or at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this material at NARA, 

call 202–741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

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: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 98–22–05, 

amendment 39–10851 (63 FR 56542, 

October 22, 1998), which is applicable 

to certain Airbus Model A320 series 

airplanes, was published in the Federal 

Register on February 6, 2004 (69 FR 

5790). The action proposed to continue 

to require repetitive inspections to 

detect fatigue cracking of the lower 

surface panel on the wing center box, 

and repair if necessary. That action also 

proposed to continue to require 

modification of the lower surface panel 

on the wing center box, which would 

constitute terminating action for the 

repetitive inspections. That action also 

proposed to reduce the compliance 

times for the inspections required by the 

existing AD. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received from a single 

commenter. 

Request To Remove Paragraph (c)(1) of 

the Proposed AD 

The commenter states that paragraph 

(c)(1) of the proposed AD (Restatement 

of Requirements of AD 98–22–05), 

conflicts with paragraph (g) of the 

proposed AD (New Requirements of 

This AD). The commenter notes that 

paragraph (c)(1) requires 

accomplishment of the modification of 

the lower surface panel on the wing 

center box per Airbus Service Bulletin 

A320–57–1043, Revision 02 or Revision 

05, if no cracking is found during the 

inspection required by paragraph (c) of 

the proposed AD, but paragraph (g) 

specifies repeating the inspection per 

Airbus Service Bulletin A320–57–1082, 

Revision 01 or Revision 03, if no 

cracking is found. The commenter adds 

that French airworthiness directive 

2002–342(B), dated June 26, 2002 

(referenced in the proposed AD), and 

French airworthiness directive 97–309–

104(B), dated October 27, 1997 

(referenced in the existing AD), issued 

by the Direction Ge ́ne ́rale de l’Aviation 

Civile, which is the airworthiness 

authority for France, require 

accomplishment of the actions specified 

in Airbus Service Bulletin A320–57–

1043, Revision 02 or Revision 05 only, 

if no cracking is found. The commenter 

asks that paragraph (c)(1) be removed 

for the reasons stated above. 

The FAA partially agrees. Paragraph 

(g) of this AD requires repeating the 

inspection required by paragraph (a) or 

(f) of the AD if no cracking is found 

during either of those inspections. The 

inspection specified in paragraph (f) is

Federal Register / Vol. 69, No. 131 / Friday, July 9, 2004 / Rules and Regulations 41399

for airplanes on which the inspection 

required by paragraph (a) has not been 

done as of the effective date of the AD, 

and accomplishment of the inspection 

constitutes terminating action for the 

requirements of paragraph (a). 

Paragraph (c)(1) specifies that 

accomplishment of the modification per 

Airbus Service Bulletin A320–57–1043, 

Revision 02 or Revision 05, also 

constitutes terminating action for the 

requirements of paragraph (a). 

Therefore, if the commenter has done 

the modification required by paragraph 

(c)(1), the repetitive inspections 

required by paragraph (g) are not 

required. We have changed paragraphs 

(f) and (g) for clarification, as follows: 

We have changed paragraph (f) to state 

‘‘For airplanes on which neither the 

inspection required by paragraph (a) of 

this AD, nor the modification required 

by paragraph (c)(1) of this AD has been 

done before the effective date of this 

AD:’’ We have changed paragraph (g) to 

add ‘‘Accomplishment of the 

modification required by paragraph 

(c)(1) of this AD terminates the 

requirements of this paragraph.’’

Additionally, the applicability of this 

AD is for Model A320 series airplanes 

on which Airbus Modification 22418 

(reference Airbus Service Bulletin 

A320–57–1043) has not been done. 

French airworthiness directive 2002–

342(B), does not require 

accomplishment of the actions specified 

in Airbus Service Bulletin A320–57–

1043, but requires accomplishment of 

the actions specified in Airbus Service 

Bulletin A320–57–1082. French 

airworthiness directive 97–309–104(B), 

was cancelled upon issuance of French 

airworthiness directive 2002–342(B). 

The applicability in French 

airworthiness directive 2002–342(B), in 

part, excludes airplanes on which the 

actions specified in Service Bulletin 

A320–57–1043 have been done. No 

change to the AD is necessary in this 

regard. 

Request To Change Compliance Time 

The commenter states that the 

compliance time for the inspection 

required by paragraph (f)(2) of the 

proposed AD specifies ‘‘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.’’ The commenter notes that the 

compliance time should be ‘‘whichever 

occurs later.’’ No justification is 

provided for this comment.

We have coordinated this issue with 

the manufacturer and determined that 

the compliance time required by 

paragraph (f)(2) of this AD should 

specify ‘‘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 later.’’ The 

referenced French airworthiness 

directive and service information did 

not provide this criterion. We have 

determined that extending the 

compliance time for the inspection will 

continue to provide an acceptable level 

of safety for the affected fleet. Paragraph 

(f)(2) of this AD has been changed 

accordingly. 

Request To Change Applicability 

The commenter states that the models 

listed in French airworthiness directive 

2002–342(B), dated June 26, 2002 

(referenced in the proposed AD), are 

Airbus Model A320–111, –211, –212, 

and –231 series airplanes. The 

commenter asks that the models listed 

in the proposed AD (Model A320 series 

airplanes) be changed to match the 

models listed in the referenced French 

airworthiness directive. 

We agree. French airworthiness 

directive 97–309–104(B), dated October 

27, 1997 (referenced in the existing AD), 

listed Model A320 series airplanes and 

has since been cancelled. Therefore, we 

have changed the models listed in this 

AD to specify Model A320–111, –211, 

–212, and –231 series airplanes. This 

change corresponds with the models 

specified in French airworthiness 

directive 2002–342(B). 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

noted above, and have determined that 

air safety and the public interest require 

adopting the AD with the changes 

described previously. These changes 

will neither increase the economic 

burden on any operator nor increase the 

scope of the AD. 

Cost Impact 

There are approximately 60 airplanes 

of U.S. registry that will be affected by 

this AD. This AD reduces 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 AD, take about 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 AD, will take about 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 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 adopted herein will 

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 final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (1) is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 

‘‘significant rule’’ under 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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (14 CFR part 39) as follows:

41400 Federal Register / Vol. 69, No. 131 / Friday, July 9, 2004 / Rules and Regulations 

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 

removing amendment 39–10851 (63 FR 

56542, October 22, 1998), and by adding 

a new airworthiness directive (AD), 

amendment 39–13718, to read as 

follows:

2004–14–09 Airbus: Amendment 39–13718. 

Docket 2002–NM–177–AD. Supersedes 

AD 98–22–05, Amendment 39–10851.

Applicability: Model A320–111, –211, 

–212, and –231 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, 

AMN–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 neither the 

inspection required by paragraph (a) of this 

AD, nor the modification required by 

paragraph (c)(1) of this AD has 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 

inspection 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 

after the effective date of this AD, 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 later. 

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. Accomplishment of the 

modification required by paragraph (c)(1) of 

this AD terminates the requirements of this 

paragraph. 

(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 Airbus 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. 

Incorporation by Reference 

(k) Unless otherwise provided in this AD, 

the actions shall be done in accordance with 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997; 

Airbus Service Bulletin A320–57–1082, 

Revision 03, dated April 30, 2002; Airbus 

Service Bulletin A320–57–1043, Revision 02, 

dated May 14, 1997; and Airbus Service 

Bulletin A320–57–1043, Revision 05, dated 

April 30, 2002; as applicable. 

(1) The incorporation by reference of 

Airbus Service Bulletin A320–57–1082,

Federal Register / Vol. 69, No. 131 / Friday, July 9, 2004 / Rules and Regulations 41401

Revision 03, dated April 30, 2002; and 

Airbus Service Bulletin A320–57–1043, 

Revision 05, dated April 30, 2002; is 

approved by the Director of the Federal 

Register in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) The incorporation by reference of 

Airbus Service Bulletin A320–57–1082, 

Revision 01, dated December 10, 1997; and 

Airbus Service Bulletin A320–57–1043, 

Revision 02, dated May 14, 1997; was 

approved previously by the Director of the 

Federal Register as of November 27, 1998 (63 

FR 56542, October 22, 1998). 

(3) Copies may be obtained from Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France. Copies may be inspected at 

the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

Note 1: The subject of this AD is addressed 

in French airworthiness directive 2002–

342(B), dated June 26, 2002.

Effective Date 

(l) This amendment becomes effective on 

August 13, 2004.

Issued in Renton, Washington, on June 29, 

2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–15372 Filed 7–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–175–AD; Amendment 

39–13715; AD 2004–14–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Airbus Model 

A310 series airplanes, that currently 

requires repetitive inspections of the 

fuselage skin to detect corrosion or 

fatigue cracking around and under the 

chafing plates of the wing root; and 

corrective actions, if necessary. That AD 

also provides an optional terminating 

action for the repetitive inspections. 

This amendment reinstates repetitive 

inspections in certain areas where 

corrosion was detected and reworked as 

required by the existing AD. The actions 

specified by this AD are intended to 

detect and correct fatigue cracks and 

corrosion around and under the chafing 

plates of the wing root, which could 

result in reduced structural integrity of 

the airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective August 13, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 13, 

2004. 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of June 3, 1998 (63 FR 23377, 

April 29, 1998).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

This information may be examined at 

the Federal Aviation Administration 

(FAA), Transport Airplane Directorate, 

Rules Docket, 1601 Lind Avenue, SW., 

Renton, Washington; or at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this material at NARA, 

call (202) 741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT:

Anthony Jopling, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2190; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 98–09–20, 

amendment 39–10501 (63 FR 23377, 

April 29, 1998), which is applicable to 

certain Airbus Model A310 series 

airplanes, was published in the Federal 

Register on December 18, 2003, (68 FR 

70479). The action proposed to continue 

require reinstating repetitive inspections 

in certain areas where corrosion was 

detected and reworked as required by 

the existing AD. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comment received from a single 

commenter. 

Request to Reference Revised Service 

Information 

The commenter states that Airbus has 

issued Revision 05 to Service Bulletin 

A310–53–2069, dated November 12, 

2002, and requests that this revision be 

included in the proposed AD as an 

acceptable source of service 

information. The commenter notes that 

Revision 05 of the service bulletin 

includes a revised repair drawing and, 

for certain airplanes, deletes an 

inspection at frame 39/stringer 35. 

The FAA concurs with the intent of 

the commenter’s request to include 

Revision 05 of the service bulletin as an 

appropriate source of service 

information. However, upon review of 

Revisions 04 and 05 of the service 

bulletin, it appears that the repair 

drawing was revised in Revision 04, and 

that the manufacturer did not remove 

the revision marks when Revision 05 of 

the service bulletin was issued. We have 

determined that Revision 05 of Airbus 

Service Bulletin A310–53–2069 adds no 

new requirements. We have revised 

paragraphs (a), (b), and (d) of this final 

rule to reference Airbus Service Bulletin 

A310–53–2069, Revision 05, dated 

November 12, 2002; and Revision 04, 

dated November 8, 2000; as additional 

appropriate sources of service 

information. 

Conclusion 

After careful review of the available 

data, including the comment noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule with the change 

previously described. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Cost Impact 

There are approximately 46 airplanes 

of U.S. registry that will be affected by 

this AD. This AD adds no new 

requirements. It requires continuation of 

repetitive inspections for airplanes 

where corrosion was detected and 

reworked at frame 39, stringer 35. The 

current costs associated with AD 98–09–

20 are reiterated in their entirety as 

follows for the convenience of affected 

operators: 

The actions that are currently 

required by AD 98–09–20 take 

approximately 68 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 

previously required actions on U.S. 

operators is estimated to be $4,420 per 

airplane, per inspection cycle.