Federal Register / Vol. 69, No. 131 / Friday, July 9, 2004 / Rules and Regulations 41391

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

Adoption of the Amendment

■ Under 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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive:

2004–14–02 Rolls-Royce Corporation 

(formerly Allison Engine Company, 

Allison Gas Turbine Division, and 

Detroit Diesel Allison): Amendment 39–

13711. Docket No. FAA–2004–18538; 

Directorate Identifier 2004–NE–29–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective July 26, 2004. 

Affected ADs 

(b) None.

Applicability 

(c) This AD applies to Rolls-Royce 

Corporation (formerly Allison Engine 

Company, Allison Gas Turbine Division, and 

Detroit Diesel Allison) (RRC) models 250–

C28, –C28B, and –C28C turboshaft engines 

with third-stage turbine wheels, part number 

(P/N) 6899383, listed by serial number (SN) 

in the following Table 1:

TABLE 1.—SNS OF AFFECTED THIRD

STAGE TURBINE WHEELS

HX91922 X523242 X523281 

HX91923 X523243 X523283 

HX91925 X523244 X523284 

HX91926 X523246 X523287 

HX91928 X523249 X523288 

HX91929 X523250 X523289 

HX91930 X523251 X523290 

HX91932 X523253 X523291 

HX91934 X523255 X523292 

HX91936 X523257 X523293 

HX91937 X523260 X523294 

HX91939 X523261 X523295 

HX91940 X523262 X523296 

HX91960 X523263 X523297 

HX91962 X523264 X523298 

TABLE 1.—SNS OF AFFECTED THIRD

STAGE TURBINE WHEELS—Continued

HX91966 X523265 X523300 

HX91976 X523266 X523305 

HX91977 X523268 X523309 

HX91979 X523269 X523313 

HX91980 X523270 X523315 

X523236 X523271 X523317 

X523237 X523273 X523319 

X523238 X523276 X523320 

X523239 X523277 N/A 

X523241 X523278 N/A 

These engines are installed on, but not 

limited to, Bell Helicopter Textron 206L–1; 

Eurocopter Deutschland BO 105 LS A–1; and 

Eurocopter Canada BO 105 LS A–3 

helicopters. 

Unsafe Condition 

(d) This AD results from three reports of 

third-stage turbine wheel blade and shroud 

failures. We are issuing this AD to prevent 

loss of power and uncommanded engine 

shutdown due to failure of the third-stage 

turbine wheel blade and shroud. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

(f) For any third-stage turbine wheel with 

fewer than 250 operating hours time since 

new (TSN) on the effective date of this AD, 

replace turbine wheel before accumulating 

300 operating hours TSN. 

(g) For any third-stage turbine wheel with 

250 or more operating hours TSN on the 

effective date of this AD, replace turbine 

wheel before accumulating an additional 50 

operating hours. 

Definition 

(h) For the purposes of this AD, a 

replacement third-stage turbine wheel is a 

turbine wheel that does not have a SN listed 

in this AD. 

(i) After the effective date of this AD, do 

not install third-stage turbine wheels that are 

listed in Table 1 of this AD, into any engine. 

Alternative Methods of Compliance 

(j) The Manager, Chicago Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Special Flight Permits 

(k) Under 14 CFR 39.23, we are prohibiting 

special flight permits for this AD. 

Material Incorporated by Reference 

(l) None. 

Related Information 

(m) Rolls-Royce Corporation Alert 

Commercial Engine Bulletin No. CEB-A–72–

2202, dated May 6, 2004, pertains to the 

subject of this AD.

Issued in Burlington, Massachusetts, on 

July 1, 2004. 

Francis A Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service.

[FR Doc. 04–15508 Filed 7–8–04; 8:45 am] 

BILLING CODE 4913–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–162–AD; Amendment 

39–13710; AD 2004–14–01] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 0070 and 0100 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Fokker Model F.28 

Mark 0100 series airplanes, that 

currently requires repetitive inspections 

of certain main landing gear (MLG) 

main fittings to detect forging defects, 

and rework of the main fittings if 

necessary. This amendment requires 

either replacement of each MLG with a 

MLG that has main fittings that have 

been inspected and reworked, or various 

one-time inspections of the main fittings 

and rework if necessary. Either of these 

actions constitutes terminating action 

for the repetitive inspections. This 

action also revises the applicability by 

adding airplanes. The actions specified 

by this AD are intended to detect forging 

defects of the MLG main fittings, which 

could lead to cracking and result in 

significant structural damage to the 

airplane and possible injury to the 

occupants. 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 a 

certain other publication, as listed in the 

regulations, was approved previously by 

the Director of the Federal Register as of 

December 20, 2001 (66 FR 63159, 

December 5, 2001).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Fokker Services B.V., P.O. Box 

231, 2150 AE Nieuw-Vennep, the 

Netherlands. This information may be

41392 Federal Register / Vol. 69, No. 131 / Friday, July 9, 2004 / Rules and Regulations 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2001–24–10, 

amendment 39–12527 (66 FR 63159, 

December 5, 2001), which is applicable 

to certain Fokker Model F.28 Mark 0100 

series airplanes, was published in the 

Federal Register on March 17, 2004 (69 

FR 12582). The action proposed to 

continue to require either replacement 

of each MLG with a MLG that has main 

fittings that have been inspected and 

reworked, or various one-time 

inspections of the main fittings and 

rework if necessary. Either of those 

actions would constitute terminating 

action for the repetitive inspections. The 

action also proposed to revise the 

applicability by adding airplanes. 

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. 

Support for the Proposed AD 

The Air Transport Association of 

America, on behalf of its members, 

generally supports the intent of the 

proposed AD. 

Request to Include an Additional 

Terminating Action 

The commenter, an operator, notes 

that its fleet of Fokker Model F.28 Mark 

0100 series airplanes is not affected by 

the proposed AD. The commenter 

suggests adding an additional 

terminating action to paragraph (f) of the 

proposed AD to allow the installation of 

Menasco main landing gear (MLG) main 

fittings made of steel, in accordance 

with Fokker Service Bulletin F100–32–

090. 

The FAA acknowledges the 

commenter’s request, but the unsafe 

condition addressed in this AD pertains 

to cracking associated with MessierDowty MLG main fittings as called out 

in the applicability statement of this 

AD. This AD is applicable to airplanes 

equipped with specific Messier-Dowty 

MLG and main fitting sub-assembly part 

numbers. This AD is not applicable to 

airplanes with MLGs and fittings 

manufactured by Menasco. No change to 

this AD is necessary. 

Change Made to This AD 

Paragraph (f)(1) of this AD has been 

reworded to comply with the Office of 

the Federal Register’s guidelines for 

material incorporated by reference. 

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 change 

previously described. 

Cost Impact 

There are approximately 70 airplanes 

of U.S. registry that will be affected by 

this AD. 

The actions that are currently 

required by AD 2001–24–10 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 

previously required actions on U.S. 

operators is estimated to be $9,100, or 

$130 per airplane, per inspection cycle. 

Should an operator rework a MLG per 

Part 1 of Fokker Service Bulletin 

SBF100–32–134, it will take 

approximately 44 work hours per 

airplane at an average labor rate of $65 

per work hour. Based on these figures, 

the cost impact of the modification is 

estimated to be $2,860 per airplane. 

Should an operator do the inspections 

specified in Messier-Dowty Service 

Bulletin F100–32–102, it will take 

approximately 2 work hours per 

airplane at an average labor rate of $65 

per work hour. Based on these figures, 

the cost impact of the inspections 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:

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 39–12527 (66 FR 

63159, December 5, 2001), and by adding 

a new airworthiness directive (AD), 

amendment 39–13710, to read as 

follows:

2004–14–01 Fokker Services B.V.:

Amendment 39–13710. Docket 2003–

NM–162–AD. Supersedes AD 2001–24–

10, Amendment 39–12527.

Applicability: Model F.28 Mark 0070 and 

0100 series airplanes, certificated in any 

category, equipped with a Messier-Dowty 

main landing gear (MLG) unit having a part 

number (P/N) with a main fitting subassembly, as listed in Table 1 of this AD.

Federal Register / Vol. 69, No. 131 / Friday, July 9, 2004 / Rules and Regulations 41393

TABLE 1.—APPLICABILITY

P/N— Which includes a Main fitting sub-assembly P/N—

201072011 ................................................................................................ 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 

201072384, or 201072389). 

201072012 ................................................................................................ 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 

201072384, or 201072389). 

201072013 ................................................................................................ 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 

201072384, or 201072389). 

201072014 ................................................................................................ 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 

201072384, or 201072389). 

201072015 ................................................................................................ 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 

201072384, or 201072389). 

201072016 ................................................................................................ 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 

201072384, or 201072389). 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect forging defects of the MLG main 

fittings, which could lead to cracking and 

result in significant structural damage to the 

airplane and possible injury to the occupants, 

accomplish the following: 

Restatement of the Requirements of AD 

2001–24–10

Initial and Repetitive Inspections 

(a) For Fokker Model F.28 Mark 0100 series 

airplanes: Before the accumulation of 1,000 

total landings on a new MLG, or within 30 

days after December 20, 2001 (the effective 

date of AD 2001–24–10, amendment 39–

12527), whichever occurs later, do an initial 

eddy current inspection on all MLG main 

fittings to detect forging defects, per MessierDowty Service Bulletin No. F100–32–101, 

including Appendices A and B, dated 

October 25, 2001. After accomplishment of 

the initial inspection, repeat the eddy current 

inspection thereafter at intervals not to 

exceed 500 landings or 6 months, whichever 

occurs first, per the service bulletin. 

Accomplishment of the actions required by 

paragraph (f) of this AD terminates the 

repetitive inspections. Although this service 

bulletin specifies to submit certain 

information to the part manufacturer, this AD 

does not include such a requirement. 

Rework 

(b) For Fokker Model F.28 Mark 0100 

series airplanes: After any inspection 

required by paragraph (a) of this AD, before 

further flight, accomplish the applicable 

actions required by paragraph (b)(1) or (b)(2) 

of this AD. 

(1) If any cracking is found within the 

limits specified in Messier-Dowty Service 

Bulletin No. F100–32–101, including 

Appendices A and B, dated October 25, 2001: 

Rework the MLG main fitting per the service 

bulletin. 

(2) If any cracking is found that exceeds the 

limits specified in Messier-Dowty Service 

Bulletin No. F100–32–101, including 

Appendices A and B, dated October 25, 2001: 

Rework the MLG main fitting per a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the Civil Aviation 

Authority—The Netherlands (CAA–NL) (or 

its delegated agent). 

Exception to Service Information 

(c) During any action required by this AD, 

if the service bulletin specifies to contact 

Messier-Dowty for an appropriate action: 

Before further flight, repair per a method 

approved by the Manager, International 

Branch, ANM–116; or the CAA–NL (or its 

delegated agent). 

New Actions Required by This AD 

Initial and Repetitive Inspections 

(d) For Fokker Model F.28 Mark 0070 

series airplanes: Before the accumulation of 

1,000 total landings on a new MLG, or within 

30 days after the effective date of this AD, 

whichever occurs later, do an initial eddy 

current inspection on all MLG main fittings 

to detect forging defects, per Messier-Dowty 

Service Bulletin No. F100–32–101, including 

Appendices A and B, dated October 25, 2001. 

After accomplishment of the initial 

inspection, repeat the inspection thereafter at 

intervals not to exceed 500 landings or 6 

months, whichever occurs first, per the 

service bulletin. Accomplishment of the 

actions required by paragraph (f) of this AD 

terminates the repetitive inspections. 

Rework 

(e) For Fokker Model F.28 Mark 0070 series 

airplanes: After any inspection required by 

paragraph (d) of this AD, before further flight, 

accomplish the applicable actions required 

by paragraph (e)(1) or (e)(2) of this AD. 

(1) If any cracking is found within the 

limits specified in Messier-Dowty Service 

Bulletin No. F100–32–101, including 

Appendices A and B, dated October 25, 2001: 

Rework the MLG main fitting per the service 

bulletin. 

(2) If any cracking is found that exceeds the 

limits specified in Messier-Dowty Service 

Bulletin No. F100–32–101, including 

Appendices A and B, dated October 25, 2001: 

Rework the MLG main fitting per a method 

approved by the Manager, International 

Branch, ANM–116; or the CAA–NL (or its 

delegated agent). 

Terminating Actions 

(f) For all airplanes: Before the 

accumulation of 16,000 total landings on a 

new MLG, do the actions in paragraph (f)(1) 

or (f)(2) of this AD. Accomplishment of 

paragraph (f)(1) or (f)(2) of this AD 

constitutes terminating action for the 

repetitive inspections required by paragraphs 

(a) and (d) of this AD.

(1) Replace the main fitting of the MLG 

with a main fitting that has had a detailed 

inspection to detect forging defects and has 

been reworked, per paragraph 2.B., Part 1, of 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF100–32–134, dated 

March 24, 2003. Any discrepancy found 

during the detailed inspection must be 

repaired before further flight per a method 

approved by the Manager, International 

Branch, ANM–116; or the CAA–NL (or its 

delegated agent). Accomplishment of the 

applicable actions in the Fokker 100 Aircraft 

Maintenance Manual and Messier-Dowty 

Component Maintenance Manual, Chapter 

32–11–04, is one approved method.

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.’’

Note 2: Fokker Service Bulletin SBF100–

32–134, dated March 24, 2003, references 

Messier-Dowty Service Bulletin F100–32–

102, including Appendices A, B, and C, 

dated February 24, 2003, as an additional 

source of service information for reworking 

the main fitting of each MLG.

(2) Do eddy current and etch penetrant 

inspections, as applicable, to detect forging 

defects; and rework the main fitting of each 

MLG, as applicable; by accomplishing all of 

the actions in paragraph 3.C. of the 

Accomplishment Instructions of MessierDowty Service Bulletin F100–32–102, 

including Appendices A, B, and C, dated 

February 24, 2003. Do all of the actions per 

the service bulletin. Any rework must be 

done before further flight. 

Parts Installation 

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

person may install a MLG, MLG main fitting 

sub-assembly, or MLG main fitting having a 

P/N listed in Messier-Dowty Service Bulletin 

F100–32–102, including Appendices A, B, 

and C, dated February 24, 2003, on any 

airplane unless the part has been inspected

41394 Federal Register / Vol. 69, No. 131 / Friday, July 9, 2004 / Rules and Regulations 

and reworked, as applicable, per that service 

bulletin. 

Alternative Methods of Compliance 

(h) 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 

(i) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Fokker Service Bulletin SBF100–32–134, 

dated March 24, 2003; Messier-Dowty 

Service Bulletin No. F100–32–101, including 

Appendices A and B, dated October 25, 2001; 

and Messier-Dowty Service Bulletin F100–

32–102, including Appendices A, B, and C, 

dated February 24, 2003; as applicable. 

(1) The incorporation by reference of 

Fokker Service Bulletin SBF100–32–134, 

dated March 24, 2003; and Messier-Dowty 

Service Bulletin F100–32–102, including 

Appendices A, B, and C, dated February 24, 

2003; 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 

Messier-Dowty Service Bulletin No. F100–

32–101, including Appendices A and B, 

dated October 25, 2001, was approved 

previously by the Director of the Federal 

Register as of December 20, 2001 (66 FR 

63159, December 5, 2001). 

(3) Copies may be obtained from Fokker 

Services B.V., P.O. Box 231, 2150 AE NieuwVennep, the Netherlands. 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 3: The subject of this AD is addressed 

in Dutch airworthiness directive 2003–040, 

dated March 31, 2003.

Effective Date 

(j) This amendment becomes effective on 

August 13, 2004.

Issued in Renton, Washington, on June 24, 

2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–15368 Filed 7–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2001–NM–352–AD; Amendment 

39–13707; AD 2004–13–25] 

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 supersedes 

an existing airworthiness directive (AD), 

applicable to certain Airbus Model 

A330, A340–200, and A340–300 series 

airplanes, that currently requires 

repetitive inspections to check the play 

of the eye-end of the piston rod of the 

elevator servo-controls, and follow-on 

corrective actions if necessary. This 

amendment requires the replacement of 

certain elevator servo-controls with 

new, improved servo-controls. The 

actions specified by this AD are 

intended to detect and correct excessive 

play of the eye-end of the piston rod of 

the elevator servo-controls, which could 

result in failure of the elevator servocontrol. This action is intended to 

address the identified unsafe condition.

DATES: Effective August 13, 2004. 

The incorporation by reference of 

certain publications, as 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 July 20, 2000 (65 FR 

37476, June 15, 2000).

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 2000–12–06, 

amendment 39–11784 (65 FR 37476, 

June 15, 2000), which is applicable to 

certain Airbus Model A330 and A340 

series airplanes, was published in the 

Federal Register on March 25, 2004 (69 

FR 15262). The action proposed to 

continue to require the replacement of 

certain elevator servo-controls with 

new, improved servo-controls. 

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 Change Applicability 

The commenter, the airplane 

manufacturer, requests that the 

applicability of the proposed AD be 

changed to match the applicability as 

shown in the French airworthiness 

directives. The commenter notes that 

the applicability of the French 

airworthiness directives lists the 

affected airplanes by specific model 

dash numbers (i.e., A330 aircraft, model 

–202, –223, –243, –301, etc.) The basis 

of the commenter’s request is to limit 

the applicability of the proposed AD to 

airplane models that either contain or 

will contain the terminating 

modification in the airplane’s type 

design, and to avoid making the 

proposed AD applicable to airplane 

models that do not have the affected 

servo-control part numbers specified in 

the proposed AD. We infer that the 

manufacturer wants to clarify that 

Airbus Model A340–541 and –642 

airplanes are not affected by the 

proposed AD. 

We partially agree with the 

commenter’s request to change the 

applicability. We have changed the 

applicability of this final rule, but it 

does not match the applicability as 

shown in the French airworthiness 

directives. To avoid accidentally 

omitting airplane models that are listed 

on a U.S. type certificate data sheet 

(TCDS), we usually identify airplane 

series instead of individual model dash 

numbers in the applicability of our AD. 

The U.S. TCDS for the Model A340 

includes the Model A340–200 series, 

comprising A340–211, –212, and –213 

airplanes; the Model A340–300 series, 

comprising A340–311, –312, and –313 

airplanes; and Model A340–541 and