Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 60799

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–13–AD; Amendment 

39–13817; AD 2004–20–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 and B4 Series Airplanes; 

Model A300 B4–600, A300 B4–600R, 

A300 F4–600R Series Airplanes, and 

A300 C4–605R Variant F Airplanes 

(Collectively Called A300–600); and 

Model A310 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Airbus Model A300 B2 

and B4 series airplanes; Model A300 

B4–600, A300 B4–600R, A300 F4–600R 

series airplanes, and A300 C4–605R 

Variant F airplanes (collectively called 

A300–600); and Model A310 series 

airplanes. This amendment requires a 

detailed inspection of certain pulleys 

and control cables in the rear fuselage 

for corrosion and damage; and 

corrective action, if necessary. This 

action is necessary to detect and correct 

frayed or corroded control cables for the 

elevator and rudder, which could result 

in a ruptured control cable, and possible 

reduced controllability of the airplane. 

This action is intended to address the 

identified unsafe condition.

DATES: Effective November 17, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

17, 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 all Airbus Model 

A300 B2 and A300 B4; Model A300 B4–

600, B4–600R, C4–605R Variant F, and 

F4–600R (collectively called A300–600); 

and Model A310 series airplanes; was 

published in the Federal Register on 

May 7, 2004 (69 FR 25511). That action 

proposed to require a detailed 

inspection of certain pulleys and control 

cables in the rear fuselage for corrosion 

and damage; and corrective action, if 

necessary. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

single comment received. 

Request To Give Credit for Actions 

Done Previously 

One commenter requests that we 

revise the proposed AD to give credit for 

actions done previously according to the 

original issue of Airbus Service Bulletin 

A300–27A0197, including Appendix 01, 

dated August 8, 2002. (The proposed 

AD refers to Airbus Service Bulletin 

A300–27A0197, Revision 01, including 

Appendix 01, dated February 26, 2003; 

as the appropriate source of service 

information for doing the proposed 

actions on Model A300 B2 and A300 B4 

series airplanes.) The commenter notes 

that the Accomplishment Instructions in 

Revision 01 of the service bulletin are 

unchanged from those in the original 

issue of the service bulletin. 

We concur. We have reviewed the 

original issue of Airbus Service Bulletin 

A300–27A0197 and concur that the 

Accomplishment Instructions are the 

same as those in Revision 01. We have 

added a new paragraph (c) to this final 

rule (and re-identified subsequent 

paragraphs accordingly) to give credit 

for actions done per the original issue of 

Airbus Service Bulletin A300–27A0197. 

Explanation of Additional Change 

We have revised the applicability 

statement of this final rule to identify 

model designations as published in the 

most recent type certificate data sheet 

for the affected models. 

Conclusion 

After careful review of the available 

data, including the comment noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

described previously. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we may 

consider further rulemaking then. 

Cost Impact 

We estimate that 174 airplanes of U.S. 

registry will be affected by this AD, and 

that it will take approximately 1 work 

hour per airplane to accomplish the 

required inspection. The average labor 

rate is $65 per work hour. Based on 

these figures, the cost impact of this AD 

on U.S. operators is estimated to be 

$11,310, or $65 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.

60800 Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 

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:

2004–20–12 Airbus: Amendment 39–13817. 

Docket 2003–NM–13–AD.

Applicability: All Model A300 B2 and B4 

series airplanes; Model A300 B4–600, A300 

B4–600R, A300 F4–600R series airplanes, 

and A300 C4–605R Variant F airplanes 

(collectively called A300–600); and Model 

A310 series airplanes; certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect and correct frayed or corroded 

control cables for the elevator and rudder, 

which could result in a ruptured control 

cable, and possible reduced controllability of 

the airplane, accomplish the following: 

Definitions 

(a) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of the following service 

bulletins, as applicable: 

(1) For Model A300 B2 and A300 B4 series 

airplanes: Airbus Service Bulletin A300–

27A0197, Revision 01, including Appendix 

01, dated February 26, 2003; 

(2) For Model A300 B4–600, A300 B4–

600R, A300 F4–600R series airplanes; and 

A300 C4–605R Variant F airplanes 

(collectively called A300–600): Airbus 

Service Bulletin A300–27A6051, including 

Appendix 01, dated August 8, 2002; and 

(3) For Model A310 series airplanes: 

Airbus Service Bulletin A310–27A2098, 

including Appendix 01, dated August 8, 

2002. 

(b) In this AD, the phrase ‘‘date of 

airworthiness certification’’ means the date of 

issuance of the original Airworthiness 

Certificate or the original Export Certificate of 

Airworthiness, whichever occurs first. 

(c) For Model A300 B2 and A300 B4 series 

airplanes: Actions accomplished before the 

effective date of this AD according to Airbus 

Service Bulletin A300–27A0197, including 

Appendix 01, dated August 8, 2002; are 

acceptable for compliance with the 

corresponding actions required by this AD. 

Inspection and Corrective Action 

(d) At the applicable time in paragraph 

(d)(1), (d)(2), (d)(3), or (d)(4) of this AD, do 

a detailed inspection for corrosion and 

damage (e.g., frayed or broken wires) of the 

pulleys and cables of the rudder, elevator, 

trimmable horizontal stabilizer, and rudder 

trim control located at the rear of the 

fuselage; including any applicable testing 

and lubrication following the inspection. If 

any corrosion or damage is found that is 

outside the limits specified in the service 

bulletin, prior to further flight, replace the 

affected cable with a new cable; including 

any applicable testing and lubrication 

following the replacement. Accomplish all 

the actions in accordance with the applicable 

service bulletin. 

(1) For airplanes that have accumulated, as 

of the effective date of this AD, less than 

20,000 total flight hours and less than 10 

years since the date of airworthiness 

certification: Inspect at the later of the times 

specified in paragraphs (d)(1)(i) and (d)(1)(ii) 

of this AD. 

(i) Prior to the accumulation of 20,000 total 

flight hours, or within 10 years since the date 

of airworthiness certification, whichever 

occurs earliest. 

(ii) Within 1,800 flight hours after the 

effective date of this AD. 

(2) For airplanes that have accumulated, as 

of the effective date of this AD, either 20,000 

or more total flight hours or more than 10 

years since the date of airworthiness 

certification, but less than 25,000 total flight 

hours and 13 years since the date of 

airworthiness certification: Inspect at the 

later of the times specified in paragraphs 

(d)(2)(i) and (d)(2)(ii) of this AD. 

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

flight hours, or within 13 years since the date 

of airworthiness certification, whichever 

occurs earliest. 

(ii) Within 1,800 flight hours after the 

effective date of this AD. 

(3) For airplanes that have accumulated, as 

of the effective date of this AD, either 25,000 

or more total flight hours or more than 13 

years since the date of airworthiness 

certification, but less than 30,000 total flight 

hours and 16 years since the date of 

airworthiness certification: Inspect at the 

later of the times specified in paragraphs 

(d)(3)(i) and (d)(3)(ii) of this AD. 

(i) Prior to the accumulation of 30,000 total 

flight hours, or within 16 years since the date 

of airworthiness certification, whichever 

occurs earliest. 

(ii) Within 1,200 flight hours after the 

effective date of this AD. 

(4) For airplanes that have accumulated, as 

of the effective date of this AD, either 30,000 

or more total flight hours or more than 16 

years since the date of airworthiness 

certification: Inspect within 600 flight hours 

after the effective date of this AD.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

Reporting 

(e) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (d) of this AD to 

Airbus, Customer Services Directorate, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; Attn: AI/SE–D32 Technical 

Data and Documentation Services, or fax: 

(+33) 5 61 93 28 06. Send the report at the 

applicable time specified in paragraph (e)(1) 

or (e)(2) of this AD. The Inspection Record 

Sheet in Appendix 01 of the applicable 

service bulletin may be used. Include the 

inspection results, a description of any 

discrepancy found, the airplane serial 

number, the number of landings and flight 

hours on the airplane, the service bulletin 

number, and the date of inspection. Under 

the provisions of the Paperwork Reduction 

Act of 1980 (44 U.S.C. 3501 et seq.), the 

Office of Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection is done after the 

effective date of this AD: Submit the report 

within 60 days after the inspection. 

(2) If the inspection was done prior to the 

effective date of this AD: Submit the report 

within 60 days after the effective date of this 

AD. 

Alternative Methods of Compliance 

(f) 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. 

Incorporation by Reference 

(g) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

Airbus Service Bulletin A300–27A0197, 

Revision 01, including Appendix 01, dated 

February 26, 2003; Airbus Service Bulletin 

A300–27A6051, including Appendix 01, 

dated August 8, 2002; and Airbus Service 

Bulletin A310–27A2098, including Appendix 

01, dated August 8, 2002; 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 directive 2002–

608(B) R1, dated January 8, 2003.

Effective Date 

(h) This amendment becomes effective on 

November 17, 2004.

Federal Register / Vol. 69, No. 197 / Wednesday, October 13, 2004 / Rules and Regulations 60801

Issued in Renton, Washington, on 

September 29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–22470 Filed 10–12–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–18602; Directorate 

Identifier 2003–NM–160–AD; Amendment 

39–13816; AD 2004–20–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 and B4 Series Airplanes; and 

Model A300 B4–600, B4–600R, and F4–

600R Series Airplanes, and Model C4–

605R Variant F Airplanes (Collectively 

Called A300–600)

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 B2 and B4 series 

airplanes; and certain Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes; and Model C4–605R 

Variant F airplanes (collectively called 

A300–600). This AD requires an 

inspection of the skin panels of the wing 

slats for damage and certain repairs, and 

applicable related investigative/

corrective actions if necessary. This AD 

is prompted by the results of an 

engineering evaluation that revealed 

that several repairs and some allowable 

damage limits specified in the structural 

repair manuals do not provide adequate 

static and/or fatigue strength for 

repaired wing slats. We are issuing this 

AD to find and fix previously done 

repairs of the wing slats that have 

inadequate static and/or fatigue 

strength, which, if not corrected, could 

result in loss of the slats and consequent 

reduced controllability of the airplane.

DATES: This AD becomes effective 

November 17, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of November 17, 2004.

ADDRESSES: For service information 

identified in this AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. You can 

examine this information 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.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Technical information: Tim Backman, 

Aerospace Engineer, International 

Branch, ANM–116, FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

Examining the Docket 

The AD docket contains the proposed 

AD, comments, and any final 

disposition. You can examine the AD 

docket on the Internet at http://

dms.dot.gov, or in person at the Docket 

Management Facility office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the DOT street address stated in the 

ADDRESSES section.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

an AD for all Airbus Model A300 B2 

and B4 series airplanes; and certain 

Airbus Model A300 B4–600, B4–600R, 

C4–605R Variant F, and F4–600R 

(collectively called A300–600) series 

airplanes. The proposed AD was 

published in the Federal Register on 

July 15, 2004 (69 FR 42368), to require 

an inspection of the skin panels of the 

wing slats for damage and certain 

repairs, and applicable related 

investigative/corrective actions if 

necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been submitted on the proposed 

AD or on the determination of the cost 

to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Explanation of Change to Applicability 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Costs of Compliance 

This AD will affect about 120 

airplanes of U.S. registry. The actions 

will take about 3 work hours per 

airplane, at an average labor rate of $65 

per work hour. Based on these figures, 

the estimated cost of the AD for U.S. 

operators is $23,400, or $195 per 

airplane. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD 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. 

For the reasons discussed above, I 

certify that this AD: 

(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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: