Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6549

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

Note 2: Repetitive inspections of the 

electrical harnesses are not required.

Terminating Action for Repetitive 

Inspections 

(b) Within 18 months after the effective 

date of this AD: Adjust the speed lacing for 

the soft covers of the escape slides/rafts 

located at door 3 Type I emergency exits, in 

accordance with paragraph 4.3 of Airbus 

AOT A330–25A3154 (for Model A330 series 

airplanes) or A340–25A4172 (for Model 

A340–200 and –300 series airplanes), both 

dated July 26, 2001; as applicable. This 

adjustment terminates the repetitive 

inspections of the parachute pins required by 

paragraph (a) of this AD.

Note 3: The AOTs reference Goodrich 

Aircraft Evacuation Systems Alert Service 

Bulletin 7A1509–25A324, dated July 16, 

2001, as an additional source of service 

information for adjusting the speed lacing.

Parts Installation 

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

person may install on any airplane an escape 

slide/raft having any P/N 7A1509–101 

through 7A1509–117 inclusive, and any 

serial number AD001 through AD0855 

inclusive, unless the parachute pin has been 

inspected and the speed lacing has been 

adjusted in accordance with paragraphs (a) 

and (b) of this AD. 

Alternative Methods of Compliance 

(d) 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 

(e) The actions shall be done in accordance 

with Airbus All Operator’s Telex A330–

25A3154, dated July 26, 2001; or Airbus All 

Operator’s Telex A340–25A4172, dated July 

26, 2001; 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 4: The subject of this AD is addressed 

in French airworthiness directives 2001–

359(B) R3, dated October 30, 2002, and 2001–

360(B) R1, dated February 6, 2002.

Effective Date 

(f) 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. 04–2682 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–NM–223–AD; Amendment 

39–13468; AD 2004–03–24] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A330–300, A340–200, and 

A340–300 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) that is 

applicable to all Airbus Model A330–

200, A330–300, A340–200, and A340–

300 series airplanes. This action 

requires a revision of the airplane flight 

manual to include procedures for a preflight elevator check before each flight, 

repetitive inspections for cracks of the 

attachment lugs of the mode selector 

valve position transducers on the 

elevator servocontrols, and corrective 

actions if necessary. This action is 

intended to advise the flightcrew of the 

potential for an undetected inoperative 

elevator, and of the action they must 

take to avoid this hazard. This action is 

necessary to ensure proper functioning 

of the elevator surfaces, and to detect 

and correct cracking of the attachment 

lugs, which could result in partial loss 

of elevator function and consequent 

reduced controllability of the airplane. 

This action is intended to address the 

identified unsafe condition.

DATES: Effective February 26, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

26, 2004. 

Comments for inclusion in the Rules 

Docket must be received on or before 

March 11, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

223–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmiarcomment@faa.gov. Comments sent 

via the Internet must contain ‘‘Docket 

No. 2003–NM–223–AD’’ in the subject 

line and need not be submitted in 

triplicate. Comments sent via fax or the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

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 

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.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: The 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, notified the FAA 

that an unsafe condition may exist on 

all Airbus Model A330–200, A330–300, 

A340–200, and A340–300 series 

airplanes. Each elevator on these 

airplanes is equipped with two 

servocontrols having three operating 

modes. A selector valve installed in 

each servocontrol enables the 

servocontrol to change between 

operating modes; the selector valve’s 

position is transmitted to the flight 

control computers by a transducer. The 

DGAC advises that several cracks of the 

transducer body at its attachment lugs 

have been detected. The affected 

transducers were installed at the 

damping positions 3CS1 and 3CS2. The 

cracks resulted in displacement of the 

transducer and consequent leakage of 

the hydraulic fluid into the affected 

servocontrol. In two cases the 

displacement of the transducer resulted 

in the elevator becoming inoperative (it 

dropped into a full down position), with 

no electronic centralized aircraft 

monitor (ECAM) warning provided to 

the flightcrew. Without an ECAM 

warning, this inoperative condition can 

be identified only if no elevator surface 

movement is detected during a preflight elevator check. Loss of elevator 

function, if not corrected, could result 

6550 Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 

in reduced controllability of the 

airplane. 

Explanation of Relevant Service 

Information 

Airbus has issued Service Bulletins 

A330–27A3115 and A340–27A4119, 

both Revision 02, dated December 30, 

2003. The service bulletins describe 

procedures for repetitive dye penetrant 

inspections for cracks of the attachment 

lugs of the mode selector valve position 

transducer on each elevator servocontrol 

installed at damping positions 3CS1 and 

3CS2. The service bulletins also provide 

procedures for replacing a cracked 

transducer with a new part and 

torqueing the bolts when the transducer 

is reinstalled. The DGAC classified the 

service bulletins as mandatory and 

issued French airworthiness directive 

F–2003–460, dated December 24, 2003, 

to ensure the continued airworthiness of 

these airplanes in France. 

The Airbus service bulletins refer to 

Goodrich Actuation Systems Inspection 

Service Bulletin SC4800–27–13 as an 

additional source of service information 

for the inspection. 

FAA’s Conclusions 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DGAC has 

kept the FAA informed of the situation 

described above. We have examined the 

findings of the DGAC, reviewed all 

available information, and determined 

that AD action is necessary for products 

of this type design that are certificated 

for operation in the United States. 

Explanation of Requirements of Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other airplanes of the same 

type design registered in the United 

States, this AD is being issued to ensure 

proper functioning of the elevator 

surfaces, and to detect and correct 

cracking of the attachment lugs of the 

mode selector valve position 

transducers on the elevator 

servocontrols, which could result in 

partial loss of elevator function and 

consequent reduced controllability of 

the airplane. This AD requires a revision 

of the airplane flight manual (AFM) to 

include procedures for a pre-flight 

elevator check, repetitive inspections for 

cracks of the attachment lugs, and 

corrective action if necessary. The 

actions are required to be accomplished 

in accordance with the Airbus service 

bulletins described previously, except 

as discussed under ‘‘Differences 

Between This AD and French 

Airworthiness Directive.’’

This AD also requires that operators 

report crack findings to Airbus. Because 

the cause of the cracking is not known, 

these required inspection reports will 

help determine the extent of the 

cracking in the affected fleet. Based on 

the results of these reports, we may 

determine that additional rulemaking is 

warranted. 

Differences Between This AD and the 

French Airworthiness Directive 

The FAA and DGAC airworthiness 

directives differ in their compliance 

times for the first repetitive inspection 

interval for airplanes already inspected 

in accordance with Revision 01 of the 

service bulletin. The DGAC allows up to 

700 flight cycles or 1,350 total flight 

cycles (whichever occurs later) for this 

interval, but this AD requires that all 

inspections be done within intervals of 

350 flight cycles. French airworthiness 

directive 2003–371—which was 

replaced by the existing French 

airworthiness directive 2003–460—

required that the inspection be done 

only one time. Therefore, for operators 

that had complied with 2003–371, the 

additional time following the initial 

inspection could provide the necessary 

time to schedule the subsequent 

repetitive inspections. Since we have 

not previously required the subject 

inspection, this AD does not provide for 

any extension of the first-repeated 

inspection interval. However, we may 

approve requests to adjust that interval, 

according to the provisions of paragraph 

(g) of this AD, if the request includes 

data that prove that the first repetitive 

interval would provide an acceptable 

level of safety.

Also, the DGAC airworthiness 

directive mandates a change to the flight 

crew operating manual (FCOM) to 

include an additional elevator pre-flight 

check. We agree with the need to check 

for proper functioning of the elevators 

before takeoff, but we have determined 

that the appropriate location for the 

procedure is in the AFM, in the 

Limitations section. We base this 

determination on the following 

considerations: 

1. The FCOM does not require FAA 

approval; therefore, FCOM changes 

cannot be mandated by an AD. 

2. It is possible that later changes to 

the FCOM made by an operator could 

result in removal of the necessary preflight check. 

3. An ECAM warning to the flightcrew 

would not be provided following an 

elevator failure. 

4. An elevator failure could result in 

reduced controllability of the airplane. 

The DGAC airworthiness directive 

specifies that the FCOM be amended 

‘‘for one or both damping servo controls 

above 1000 FC since new.’’ However, 

this AD requires that the parallel change 

to the AFM—which applies across 

airplane model/series—be incorporated 

within 30 days. 

Interim Action 

We consider this AD interim action. 

The manufacturer is considering 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

may consider additional rulemaking. 

Determination of Rule’s Effective Date 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

Although this action is in the form of 

a final rule that involves requirements 

affecting flight safety and, thus, was not 

preceded by notice and an opportunity 

for public comment, comments are 

invited on this rule. Interested persons 

are invited to comment on this rule by 

submitting such written data, views, or 

arguments as they may desire. 

Communications shall identify the 

Rules Docket number and be submitted 

in triplicate to the address specified 

under the caption ADDRESSES. All 

communications received on or before 

the closing date for comments will be 

considered, and this rule may be 

amended in light of the comments 

received. Factual information that 

supports the commenter’s ideas and 

suggestions is extremely helpful in 

evaluating the effectiveness of the AD 

action and determining whether 

additional rulemaking action would be 

needed. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues.

• For each issue, state what specific 

change to the AD is being requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6551

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the rule that might suggest a need to 

modify the rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report that 

summarizes each FAA-public contact 

concerned with the substance of this AD 

will be filed in the Rules Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this rule must 

submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2003–NM–223–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

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. 

The FAA has determined that this 

regulation is an emergency regulation 

that must be issued immediately to 

correct an unsafe condition in aircraft, 

and that it is not a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. It has been determined 

further that this action involves an 

emergency regulation under DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979). If it is 

determined that this emergency 

regulation otherwise would be 

significant under DOT Regulatory 

Policies and Procedures, a final 

regulatory evaluation will be prepared 

and placed in the Rules Docket. A copy 

of it, if filed, 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:

2004–03–24 Airbus: Amendment 39–13468. 

Docket 2003–NM–223–AD.

Applicability: All Model A330–200, A330–

300, A340–200, and A340–300 series 

airplanes; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To ensure proper functioning of the 

elevator surfaces, and to detect and correct 

cracking of the attachment lugs of the mode 

selector valve position transducers on the 

elevator servocontrols, which could result in 

partial loss of elevator function and 

consequent reduced controllability of the 

airplane, accomplish the following: 

AFM Revision 

(a) Within 30 days after the effective date 

of this AD, revise the Limitations section of 

the airplane flight manual (AFM) to include 

a pre-flight elevator check, by including the 

following language. This may be done by 

inserting a copy of this AD into the 

applicable AFM. Thereafter perform the preflight check before every flight in accordance 

with the procedure.

Prior or During Taxi:

‘‘FLIGHT CONTROLS CHECK

1. AT A CONVENIENT STAGE, PRIOR TO 

OR DURING TAXI, AND BEFORE 

ARMING THE AUTOBRAKE, THE PF 

SILENTLY APPLIES FULL 

LONGITUDINAL AND LATERAL 

SIDESTICK DEFLECTION. ON THE F/CTL 

PAGE, THE PNF CHECKS FULL TRAVEL 

OF ALL ELEVATORS AND ALL 

AILERONS, AND THE CORRECT 

DEFLECTION AND RETRACTION OF ALL 

SPOILERS. THE PNF CALLS OUT ‘‘FULL 

UP,’’ ‘‘FULL DOWN,’’ ‘‘NEUTRAL,’’

‘‘FULL LEFT,’’ ‘‘FULL RIGHT,’’

‘‘NEUTRAL,’’ AS EACH FULL TRAVEL/

NEUTRAL POSITION IS REACHED. THE 

PF SILENTLY CHECKS THAT THE PNF 

CALLS ARE IN ACCORDANCE WITH THE 

SIDESTICK ORDER.

NOTE: IN ORDER TO REACH FULL 

TRAVEL, FULL SIDESTICK MUST BE 

HELD FOR A SUFFICIENT PERIOD OF 

TIME.

2. THE PF PRESSES THE PEDAL DISC 

PUSHBUTTON ON THE NOSEWHEEL 

TILLER, AND SILENTLY APPLIES FULL 

LEFT RUDDER, FULL RIGHT RUDDER, 

AND NEUTRAL. THE PNF CALLS OUT 

‘‘FULL LEFT,’’ ‘‘FULL RIGHT,’’

‘‘NEUTRAL,’’ AS EACH FULL TRAVEL/

NEUTRAL POSITION IS REACHED.

3. THE PNF APPLIES FULL 

LONGITUDINAL AND LATERAL 

SIDESTICK DEFLECTION, AND SILENTLY 

CHECKS FULL TRAVEL AND CORRECT 

SENSE OF ALL ELEVATORS AND ALL 

AILERONS, AND CORRECT DEFLECTION 

AND RETRACTION OF ALL SPOILERS, 

ON THE ECAM F/CTL PAGE.’’

Note 1: Full and complete elevator travel 

(position commanded) can be verified on the 

ECAM Flight Control Page. A determination 

of ‘‘correct sense’’ should include verification 

that there is complete and full motion of the 

sidesticks without binding.

(b) If any pre-flight check required by 

paragraph (a) of this AD reveals improper 

function of the elevator: Before further flight, 

perform the inspections required by 

paragraph (c) of this AD. 

Inspections 

(c) At the applicable time specified in 

paragraph (c)(1) or (c)(2) of this AD, except 

as required by paragraph (b) of this AD: 

Perform a dye penetrant inspection of the 

attachment lugs of the mode selector valve 

position transducers on each elevator 

servocontrol installed at damping positions 

3CS1 and 3CS2. Do the inspection in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330–

27A3115 or A340–27A4119, both Revision 

02, both dated December 30, 2003, as 

applicable (hereafter ‘‘the service bulletin’’). 

An inspection that is done before the 

effective date of this AD is acceptable for 

compliance with the initial inspection 

requirement of this paragraph, if the 

inspection is done in accordance with any of 

the following Airbus All Operators Telexes 

(AOTs): AOT A330–27A3115 or A340–

27A4119, dated September 11, 2003, or 

Revision 01 of each AOT dated September 

25, 2003; as applicable. Repeat the inspection 

thereafter at intervals not to exceed 350 flight 

cycles. 

(1) If the age of the servocontrol from the 

date of its first installation on the airplane 

can be positively determined: Do the 

inspection before the accumulation of 1,000 

total flight cycles on the elevator 

servocontrol, or within 350 flight cycles on 

the servocontrol after the effective date of 

this AD, whichever occurs later. 

(2) If the age of the servocontrol from the 

date of its first installation on the airplane 

cannot be positively determined, do the 

inspection within 350 flight cycles on the 

servocontrol after the effective date of this 

AD.

Note 2: The service bulletin refers to 

Goodrich Actuation Systems Inspection 

Service Bulletin SC4800–27–13 as an 

additional source of service information for 

the inspection.

Corrective Actions 

(d) If any crack is found during any 

inspection required by paragraph (c) of this 

AD: Before further flight, replace either the 

transducer or servocontrol with a new part, 

in accordance with the service bulletin. 

Reporting Requirement 

(e) If any crack is found during any 

inspection required by paragraph (c) of this 

AD: Submit a report in accordance with the 

service bulletin at the applicable time(s) 

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

this AD: Submit reports to Airbus Customer 

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,