31874 Federal Register / Vol. 69, No. 110 / Tuesday, June 8, 2004 / Rules and Regulations 

Actions Compliance Procedures 

(1) Using a flourescent dye-penetrant or dye-check 

method, inspect the airbrake torque tube for cracks 

and corrosion pits. Visually inspect for permanent 

distortions and surface corrosion (damage). 

Within the next 25 hours time-in-service 

(TIS) after July 19, 2004 (the effective 

date of this AD). Repetitively inspect 

thereafter at intervals not to exceed 12 

calendar months or 100 hours TIS, 

whichever occurs later.

Follow Allstar PZL Glider SP. Z o.o. Mandatory Bulletin No. BE–052/SZD–50–3/

2003 ‘‘Puchacz’’, dated July 22, 2003. 

(2) Based on the results of the inspection: (a) Repair 

the airbrake torque tube if slight, uniform corrosive 

deposits are found during the inspection required in 

paragraph (e)(1) of this AD by removing the corrosive deposits with a fine abrasive paper; and (b) 

Replace the airbrake torque tube if any other damage is found during the inspection required in paragraph (e)(1) of this AD. 

Prior to further flight after the inspection in 

which the damage is found. Continue 

with the repetitive inspections required 

in paragraph (e)(1) of this AD after each 

repair or replacement is made.

Follow Allstar PZL Glider Sp. Z o.o. Mandatory Bulletin No. BE–052/SZD–50–3/

2003 ‘‘Puchacz’’, dated July 22, 2003. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, contact Greg Davison, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4130; facsimile: 

(816) 329–4090. 

Does This AD Incorporate Any Material by 

Reference? 

(g) You must do the actions required by 

this AD following the instructions in Allstar 

PZL Glider Sp. Z o.o. Mandatory Bulletin No. 

BE–052/SZD–50–3/2003 ‘‘Puchacz’’, dated 

July 22, 2003. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

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

part 51. You may get a copy from Allstar PZL 

Glider Sp. z o.o., ul. Cieszyn ́ ska 325, 43–300 

Bielsko-Biala. You may review copies at 

FAA, Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; 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. 

Is There Other Information That Relates to 

This Subject? 

(h) Republic of Poland AD Number SP–

0052–2003–A, dated July 22, 2003, also 

addresses this subject.

Issued in Kansas City, Missouri, on May 

27, 2004. 

Scott L. Sedgwick, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–12573 Filed 6–7–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–111–AD; Amendment 

39–13654; AD 2004–11–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330, A340–200, and A340–300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Airbus Model 

A330, A340–200, and A340–300 series 

airplanes, that requires replacement of 

flap rotary actuators with modified flap 

rotary actuators. This action is necessary 

to prevent fatigue failure of the rotary 

actuator lever for the flaps, which could 

result in loss of the flap surface and 

consequent reduced controllability of 

the airplane. This action is intended to 

address the identified unsafe condition.

DATES: Effective July 13, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of July 13, 

2004.

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) to 

include an airworthiness directive (AD) 

that is applicable to certain Airbus 

Model A330, A340–200, and A340–300 

series airplanes was published in the 

Federal Register on February 13, 2004 

(69 FR 7181). That action proposed to 

require replacement of flap rotary 

actuators with modified flap rotary 

actuators. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. The FAA 

has duly considered the comments 

received. 

Request To Reference Latest Revisions 

of Service Information 

One commenter, the airplane 

manufacturer, requests that we revise 

the proposed AD to refer to Airbus 

Service Bulletins A330–27–3106 (for 

Model A330 series airplanes) and A340–

27–4111 (for Model A340–200 and –300 

series airplanes), both Revision 02, both 

dated February 4, 2004. The proposed 

AD refers to the original issue of those 

service bulletins, dated February 18, 

2003, as the acceptable sources of 

service information for the 

accomplishment of the proposed 

actions. 

We concur with the commenter’s 

request. The procedures in Revision 01, 

dated April 8, 2003, and Revision 02 of 

the referenced service bulletins are 

essentially the same as those in the 

Federal Register / Vol. 69, No. 110 / Tuesday, June 8, 2004 / Rules and Regulations 31875

original issue of the service bulletins. 

Revision 02 of the service bulletins adds 

references to Liebherr-Aerospace 

Lindenberg GmbH Service Bulletins 

697510–27–03 and 697511–27–03, both 

dated December 5, 2003, as additional 

sources of service information for 

replacing the subject flap rotary 

actuators. Accordingly, we have revised 

paragraph (a) of this AD to refer to 

Revision 02 of the Airbus service 

bulletins as the appropriate sources of 

service information for accomplishment 

of the required actions. We have also 

added a new paragraph (b) (and 

reidentified subsequent paragraphs 

accordingly) to state that replacements 

accomplished before the effective date 

of this AD per the original issue or 

Revision 01 of the service bulletins are 

acceptable for compliance with this AD. 

Also, we have revised Note 1 of this AD 

to add references to the new LiebherrAerospace Lindenberg GmbH service 

bulletins. 

Request To Revise Compliance 

Threshold 

The same commenter requests that we 

revise the proposed AD to make the 

compliance threshold for the proposed 

actions consistent with that specified in 

the parallel French airworthiness 

directives. The commenter notes that, 

while paragraph (a) of the proposed AD 

specifies doing the replacement at the 

later of the times specified in 

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

French airworthiness directives 2003–

140(B) and 2003–141(B), both dated 

April 2, 2003, specify doing the 

replacement at the earlier of those times. 

We concur. The reference to the 

‘‘later’’ of the times in paragraphs (a)(1) 

and (a)(2) of the proposed AD was 

inadvertent, and was due to a 

misinterpretation of the French 

airworthiness directives. We intend the 

requirements of this AD and the 

compliance times for those 

requirements to be the same as those in 

the parallel French airworthiness 

directives. (We state no difference from 

the French airworthiness directives in 

the proposed AD.) We have revised 

paragraph (a) of this AD to require 

compliance at the earlier of the times 

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

of this AD. We have determined that no 

U.S.-registered airplane is close to the 

compliance threshold, so this change 

should not increase the economic 

burden on any operator. 

Difference Between the French 

Airworthiness Directive and This AD 

The applicability of French 

airworthiness directives 2003–140(B) 

and 2003–141(B), both dated April 2, 

2003, excludes airplanes on which 

Airbus Service Bulletin A330–27–3106 

(for Model A330 series airplanes) or 

A340–27–4111 (for Model A340–200 

and –300 series airplanes) has been 

accomplished in service. However, we 

have not excluded those airplanes from 

the applicability of this AD. Rather, this 

AD includes a requirement to 

accomplish the actions specified in 

those service bulletins. Such a 

requirement ensures that the actions 

specified in the service bulletins and 

required by this AD are accomplished 

on all affected airplanes. Operators must 

continue to operate the airplane in the 

configuration required by this AD 

unless an alternative method of 

compliance is approved. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Cost Impact 

We estimate that 9 airplanes of U.S. 

registry will be affected by this AD, that 

it will take approximately 45 work 

hours per airplane to accomplish the 

required replacement, and that the 

average labor rate is $65 per work hour. 

Required parts will cost approximately 

$35,000 per airplane. Based on these 

figures, the cost impact of this AD on 

U.S. operators is estimated to be 

$341,325, or $37,925 per airplane. 

The cost impact figure discussed 

above is 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:

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:

2004–11–08 Airbus: Amendment 39–13654. 

Docket 2003–NM–111–AD.

Applicability: Model A330, A340–200, and 

A340–300 series airplanes; except for those 

on which Airbus Modification 50044 has 

been accomplished in production, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent fatigue failure of the rotary 

actuator lever for the flaps, which could 

result in loss of the flap surface and 

consequent reduced controllability of the 

airplane, accomplish the following: 

Replacement 

(a) Replace the flap rotary actuators with 

modified flap rotary actuators in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–27–3106 (for 

Model A330 series airplanes) or A340–27–

4111 (for Model A340–200 and –300 series 

airplanes), both Revision 02, both dated 

February 4, 2004, as applicable. Do the 

replacement at the earlier of the times 

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

this AD. 

31876 Federal Register / Vol. 69, No. 110 / Tuesday, June 8, 2004 / Rules and Regulations 

(1) Prior to the accumulation of 18,000 

total flight cycles. 

(2) Within 12 years since the date of 

issuance of the original Airworthiness 

Certificate, or within 12 years since the date 

of issuance of the original Export Certificate 

of Airworthiness, whichever occurs first. 

(b) Replacements accomplished before the 

effective date of this AD in accordance with 

Airbus Service Bulletin A330–27–3106 (for 

Model A330 series airplanes) or A340–27–

4111 (for Model A340–200 and –300 series 

airplanes), both dated February 18, 2003; or 

Revision 01 of those service bulletins, both 

dated April 8, 2003; as applicable; are 

acceptable for compliance with paragraph (a) 

of this AD.

Note 1: Airbus Service Bulletins A330–27–

3106 and A340–27–4111, both Revision 02, 

reference Liebherr-Aerospace Lindenberg 

GmbH Service Bulletins 697510–27–02 and 

697511–27–02, both dated February 21, 2003; 

and Liebherr-Aerospace Lindenberg GmbH 

Service Bulletins 697510–27–03 and 697511–

27–03, both dated December 5, 2003; as 

additional sources of service information for 

accomplishment of the replacement.

Alternative Methods of Compliance 

(c) 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 (AMOCs) for this AD. 

Incorporation by Reference 

(d) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Airbus Service Bulletin A330–27–3106, 

Revision 02, dated February 4, 2004; or 

Airbus Service Bulletin A340–27–4111, 

Revision 02, dated February 4, 2004; as 

applicable. 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 directives 2003–

140(B), dated April 2, 2003, and 2003–

141(B), dated April 2, 2003.

Effective Date 

(e) This amendment becomes effective on 

July 13, 2004.

Issued in Renton, Washington, on May 20, 

2004. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–12572 Filed 6–7–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–323–AD; Amendment 

39–13657; AD 2004–11–11] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–600, 737–700, 737–700C, 

737–800, and 737–900 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Boeing Model 737–

600, 737–700, 737–700C, 737–800, and 

737–900 series airplanes, that requires, 

for certain airplanes, installation of 

screws and spacers to secure the wire 

bundles for the aft fuel boost pumps of 

the main fuel tanks. For certain other 

airplanes, this amendment requires a 

general visual inspection of the wire 

bundles to determine if the wire 

bundles are clamped, and/or if they are 

damaged; further investigation, as 

applicable; repair of any damage; and 

installation of applicable brackets, 

clamps, and spacers to secure the wire 

bundles. This action is necessary to 

prevent electrical arcing in a fuel 

leakage zone, which could result in an 

uncontrolled fire. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective July 13, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of July 13, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 

98124–2207. 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:

Doug Pegors, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6504; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Boeing 

Model 737–600, 737–700, 737–700C, 

737–800, and 737–900 series airplanes 

was published in the Federal Register

on March 5, 2004 (69 FR 10357). That 

action proposed to require for certain 

airplanes, installation of screws and 

spacers to secure the wire bundles for 

the aft fuel boost pumps of the main fuel 

tanks. For certain other airplanes, that 

action proposed to require a general 

visual inspection of the wire bundles to 

determine if the wire bundles are 

clamped, and/or if they are damaged; 

further investigation, as applicable; 

repair of any damage; and installation of 

applicable brackets, clamps, and spacers 

to secure the wire bundles. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

We have determined that air safety 

and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

There are approximately 1,284 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

527 airplanes of U.S. registry will be 

affected by this AD. The work hours and 

required parts per airplane vary 

according to the configuration group to 

which the affected airplane belongs. The 

average labor rate is $65 per work hour. 

The following table shows the 

estimated cost impact for airplanes 

affected by this AD: