6552 Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 

Services, Engineering and Technical Support, 

Attention: J. Laurent, SEE53, fax +33/

(0)5.61.93.44.25, Sita Code TLSBQ7X. 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) For an initial inspection done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(2) For an inspection done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

Parts Installation 

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

person may install the following part on any 

airplane: a transducer, or a transducer fitted 

on an elevator servocontrol, in the operator’s 

inventory before September 25, 2003, unless 

that transducer has been inspected in 

accordance with the service bulletin and is 

crack-free. 

Alternative Methods of Compliance 

(g) 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 

(h) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

Airbus Service Bulletin A330–27A3115, 

Revision 02, including Appendix 01, dated 

December 30, 2003; or Airbus Service 

Bulletin A340–27A4119, Revision 02, 

including Appendix 01, dated December 30, 

2003; 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 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC.

Note 3: The subject of this AD is addressed 

in French airworthiness directive F–2003–

460, dated December 24, 2003.

Effective Date 

(i) This amendment becomes effective on 

February 26, 2004.

Issued in Renton, Washington, on February 

2, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2683 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–283–AD; Amendment 

39–13470; AD 2004–03–26] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Falcon 900EX Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Dassault Model 

Falcon 900EX series airplanes, that 

requires modification of the front 

attachment area of the No. 2 engine. 

This action is necessary to prevent 

failure of the fail-safe lugs of the 

hoisting plate of the forward engine 

mount, and subsequent cracking of the 

pick-up folded sheet of the pylon 

forward rib. Such cracking could 

rupture the mast case box, which could 

result in loss of the two forward engine 

mounts and consequent separation of 

the engine from the airplane. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective March 17, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of March 17, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Dassault Falcon Jet, PO Box 2000, 

South Hackensack, New Jersey 07606. 

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 Office of 

the Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

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) to 

include an airworthiness directive (AD) 

that is applicable to certain Dassault 

Model Falcon 900EX series airplanes 

was published in the Federal Register

on October 9, 2003 (68 FR 58285). That 

action proposed to require modification 

of the front attachment area of the No. 

2 engine. 

Comment 

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 Add Revised Service 

Information 

The commenter asks that the 

proposed AD be changed to cite only 

Dassault Service Bulletin F900EX–103, 

Revision 1, dated October 16, 2002, as 

the appropriate source of service 

information for accomplishment of the 

modification. (The original issue of the 

service bulletin was cited as the 

appropriate source of service 

information for accomplishment of the 

modification in the proposed AD.) The 

commenter states that there are some 

build differences on airplanes with 

serial numbers 1 through 4 inclusive, 

that do not exist on other airplanes 

specified in the applicability of the 

original issue of the service bulletin; 

therefore, the original issue cannot be 

used for airplanes with those serial 

numbers. Revision 1 describes 

additional procedures for the 

modification of airplanes with serial 

numbers 1 through 4. The commenter 

adds that the Direction Ge ́ne ́rale de 

l’Aviation Civile, which is the 

airworthiness authority for France, has 

been informed of this change and has 

agreed not to issue a revision to French 

airworthiness directive 2001–160–

027(B), dated May 2, 2001 (referenced in 

the proposed AD), due to inclusion of 

the phrase ‘‘original issue or further 

approved revisions’’ in that 

airworthiness directive. 

The FAA agrees with the commenter. 

We have added Revision 1 of the service 

bulletin, and we have changed all 

service bulletin references in this final 

rule to specify Revision 1. 

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 

described previously. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Cost Impact 

We estimate that 36 airplanes of U.S. 

registry will be affected by this AD, that 

it will take about 85 work hours per 

airplane to accomplish the modification, 

Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6553

and that the average labor rate is $65 per 

work hour. Required parts will cost 

about $14,479 per airplane. Based on 

these figures, the cost impact of the 

modification on U.S. operators is 

estimated to be $720,144, or $20,004 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:

2004–03–26 Dassault Aviation:

Amendment 39–13470. Docket 2001–

NM–283–AD.

Applicability: Model Falcon 900EX series 

airplanes, serial numbers 1 through 60 

inclusive; certificated in any category; except 

those on which Dassault Modifications 

M2754 and M2925, identified in Dassault 

Service Bulletin F900EX–103, Revision 1, 

dated October 16, 2002, have been 

accomplished. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the fail-safe lugs of 

the forward engine mount, and consequent 

cracking of the pick-up folded sheet of the 

pylon forward rib, which could rupture the 

mast case box and result in loss of the two 

forward engine mounts and consequent 

separation of the engine from the airplane, 

accomplish the following: 

Modification 

(a) Prior to the accumulation of 3,750 flight 

cycles since the date of issuance of the 

original Airworthiness Certificate or the date 

of issuance of the Export Certificate of 

Airworthiness, whichever occurs first: 

Modify the front attachment area of the No. 

2 engine by doing all the actions per 

Paragraphs 2.A. through 2.D. of the 

Accomplishment Instructions of Dassault 

Service Bulletin F900EX–103, Revision 1, 

dated October 16, 2002. 

Alternative Methods of Compliance 

(b) 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 

(c) The actions shall be done in accordance 

with Dassault Service Bulletin F900EX–103, 

Revision 1, dated October 16, 2002. 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 

Dassault Falcon Jet, P.O. Box 2000, South 

Hackensack, New Jersey 07606. Copies may 

be inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the Federal 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC.

Note 1: The subject of this AD is addressed 

in French airworthiness directive 2001–160–

027(B), dated May 2, 2001.

Effective Date 

(d) This amendment becomes effective on 

March 17, 2004.

Issued in Renton, Washington, on February 

3, 2004. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2684 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–CE–38–AD; Amendment 

39–13473; AD 2004–03–29] 

RIN 2120–AA64 

Airworthiness Directives; Pacific 

Aerospace Corporation, Ltd. Models 

FU24–954 and FU24A–954 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for all 

Pacific Aerospace Corporation, Ltd. 

Models FU24–954 and FU24A–954 

airplanes. This AD requires you to 

perform repetitive detailed visual 

inspections of the forward vertical fin 

base for cracks. If any cracks or 

discrepancies are found, you must 

repair the structure before further flight 

and notify the FAA. This AD is the 

result of mandatory continuing 

airworthiness information (MCAI) 

issued by the airworthiness authority for 

New Zealand. We are issuing this AD to 

detect and correct cracks in the vertical 

fin base, which could result in loss of 

the fin and loss of aircraft control.

DATES: This AD becomes effective on 

April 19, 2004.

ADDRESSES: You may view the AD 

docket at FAA, Central Region, Office of 

the Regional Counsel, Attention: Rules 

Docket No. 2003–CE–38–AD, 901 

Locust, Room 506, Kansas City, 

Missouri 64106. Office hours are 8 a.m. 

to 4 p.m., Monday through Friday, 

except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, 

Small Airplane Directorate, 901 Locust, 

Room 302, Kansas City, MO 64106; 

telephone: 816–329–4146; facsimile: 

816–329–4090.

SUPPLEMENTARY INFORMATION:

Discussion 

What events have caused this AD?

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

New Zealand, notified the FAA of an 

unsafe condition that may exist on all