71452 Federal Register / Vol. 67, No. 231 / Monday, December 2, 2002 / Rules and Regulations 

New Requirements of this AD 

Cadmium Plating Applied During Production 

(c) For airplanes on which cadmium 

plating of the forward four bolt holes was 

applied during production: No further action 

is required by this AD. If operator records 

indicate that during the inspection required 

by paragraph (a) of this AD cadmium plating 

was applied during production (not during 

rework or replating), no further action is 

required by this AD. (Indications of rework 

include oversized fasteners and/or fasteners 

with repair sleeves, and/or flap track dash 

numbers that have been changed per the 

service bulletin.) 

Compliance Time for Borescope Inspection 

(d) For airplanes on which cadmium 

plating of the forward four bolt holes was not

applied during production: Do the action 

required by paragraph (e) of this AD at the 

later of the times given in paragraphs (d)(1) 

and (d)(2) of this AD. 

(1) Within 2 years or 2,000 flight cycles 

after the effective date of this AD, whichever 

is first; or 

(2) Within 6 years after doing the initial 

bolt hole rework per AD 91–03–17. 

Borescope Inspection 

(e) Do a borescope inspection of the 

forward four bolt holes on each side of the 

fail-safe bar of the flap tracks of the trailing 

edge flaps for discrepancies (corrosion, 

cracks, damaged cadmium plating), per Part 

2 of the Work Instructions of Boeing Service 

Bulletin 747–57–2256, Revision 3, dated June 

21, 2001. Then, do the actions specified in 

paragraph (e)(1), (e)(2), or (e)(3) of this AD, 

as applicable, and repeat the borescope 

inspection every 8 years or 8,000 flight 

cycles, whichever is first. Accomplishment of 

the actions specified in this paragraph 

terminates the requirements of paragraph (a) 

of this AD. 

Corrective Actions 

(1) If the cadmium plating is damaged, but 

no corrosion or cracking is found: Before 

further flight, do the eddy current inspection 

specified in and per Part 2.F. of the Work 

Instructions of the service bulletin. If no 

cracking is found, before further flight, 

cadmium plate the affected bolt holes per 

Part 2.F. of the Work Instructions of the 

service bulletin. 

(2) If any corrosion is found, before further 

flight, rework the affected bolt holes as 

specified in and per Part 2.G. of the Work 

Instructions of the service bulletin. 

(3) If any cracking is found, before further 

flight, repair per a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), or per data meeting the type 

certification basis of the airplane approved 

by a Boeing Company Designated 

Engineering Representative who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved by the Manager, Seattle ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically reference 

this AD. 

Alternative Methods of Compliance 

(f)(1) An alternative method of compliance 

or adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Seattle 

ACO. Operators shall submit their requests 

through an appropriate FAA Principal 

Maintenance Inspector, who may add 

comments and then send it to the Manager, 

Seattle ACO. 

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

91–03–17, amendment 39–6884, are 

approved as alternative methods of 

compliance with paragraphs (a) and (b) of 

this AD.

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Seattle ACO.

Special Flight Permits 

(g) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Incorporation by Reference 

(h) Except as provided by paragraph (e)(3) 

of this AD, the actions shall be done in 

accordance with Boeing Service Bulletin 

747–57–2256, dated March 8, 1990; Boeing 

Service Bulletin 747–57–2256, Revision 1, 

dated November 15, 1990; Boeing Service 

Bulletin 747–57–2256, Revision 2, dated 

March 5, 1992; or Boeing Service Bulletin 

747–57–2256, Revision 3, dated June 21, 

2001; as applicable. This incorporation by 

reference is 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 Boeing Commercial Airplane 

Group, P.O. Box 3707, Seattle, Washington 

98124–2207. 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. 

Effective Date 

(i) This amendment becomes effective on 

January 6, 2003.

Issued in Renton, Washington, on 

November 19, 2002. 

Vi L. Lipski, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 02–30026 Filed 11–29–02; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NM–417–AD; Amendment 

39–12963; AD 2002–23–19] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Falcon 2000 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to all Dassault Model Falcon 

2000 series airplanes, and certain 

Dassault Model Falcon 900EX and 

Mystere Falcon 900 series airplanes. 

That AD currently requires repetitive 

operational tests of the flap asymmetry 

detection system to verify proper 

functioning, and repair, if necessary; 

repetitive replacement of the inboard 

flap jackscrews with new or 

reconditioned jackscrews; and repetitive 

measurement of the screw/nut play of 

the jackscrews on the inboard and 

outboard flaps to detect discrepancies, 

and corrective action if necessary. This 

amendment removes Model 900EX and 

Mystere Falcon 900 series airplanes 

from the applicability of the existing 

AD. For Model Falcon 2000 series 

airplanes, this amendment also adds 

certain repetitive measurements, deletes 

certain repetitive measurements, and 

extends the interval for repetitive 

replacement of certain jackscrews. This 

amendment is prompted by issuance of 

mandatory continuing airworthiness 

information by a foreign civil 

airworthiness authority. The actions 

specified by this AD are intended to 

prevent jamming of the flap jackscrews 

during the approach to landing, which 

could result in inability to move the 

flaps or an asymmetric flap condition, 

and consequent reduced controllability 

of the airplane.

DATES: Effective January 6, 2003. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of January 6, 

2003.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Dassault Falcon Jet, P.O. 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 

Federal Register / Vol. 67, No. 231 / Monday, December 2, 2002 / Rules and Regulations 71453

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) 

by superseding AD 99–14–07, 

amendment 39–11218 (64 FR 36561, 

July 7, 1999), was published in the 

Federal Register on February 15, 2002 

(67 FR 7093). The proposal is applicable 

to all Dassault Model Falcon 2000 series 

airplanes; whereas, AD 99–14–07 was 

applicable to all Dassault Model Falcon 

2000 series airplanes, and certain 

Dassault Model Falcon 900EX and 

Mystere Falcon 900 series airplanes. 

The action proposed to supersede AD 

99–14–07 to continue to require the 

following: 

• Repetitive operational tests of the 

flap asymmetry detection system to 

verify proper functioning, and repair, if 

necessary; 

• Repetitive replacement of the 

inboard flap jackscrews with new or 

reconditioned jackscrews; and 

• Repetitive measurement of the 

screw/nut play of the outboard and 

center flap jackscrews to detect 

discrepancies, and corrective action, if 

necessary. 

The action also proposed to remove 

Model 900EX and Mystere Falcon 900 

series airplanes from the applicability of 

the existing AD. For Model Falcon 2000 

series airplanes, the action also 

proposed to add certain repetitive 

measurements, delete certain repetitive 

measurements, and extend the interval 

for repetitive replacement of certain 

jackscrews. 

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. 

Request To Add Part Numbers 

One commenter requests adding 

‘‘Amdt A’’ to the jackscrew part 

numbers (P/Ns) that are already 

specified by the proposed AD (i.e., P/Ns 

5318–1, 1–5319–1, and 2–5319–1). We 

concur with the commenter’s request, 

noting that the designation of ‘‘Amdt A’’

simply indicates a reconditioned 

jackscrew that has been reidentified. As 

such, we have determined that this 

change further clarifies, but does not 

change, the requirements of this AD. In 

light of this, we have added P/Ns 5318–

1 Amdt A, 1–5319–1 Amdt A, and 2–

5319–1 Amdt A, as appropriate, for 

those P/Ns that have been reconditioned 

and reidentified. We have revised the 

applicable P/Ns in paragraphs (b) 

through (h) of the final rule accordingly. 

Request To Revise Airplane 

Maintenance Manual References 

The same commenter requests that the 

final rule reference only Chapter 5–40 of 

the Airplane Maintenance Manual 

(AMM) for the operational testing, 

inspections, and replacement action. 

The commenter adds that operators are 

managing the jackscrew life limits and 

inspections, and have planned the 

spares and maintenance inspections 

based on the actions required by AD 99–

14–07. The commenter considers that 

the corrective action can be 

accomplished only per Chapter 5–40 of 

the AMM. 

We do not concur with the 

commenter’s request that only Chapter 

5–40 of the AMM should be cited in the 

final rule as the appropriate source of 

service information for the actions 

required by the AD. In order to 

accomplish the requirements of the AD, 

it is necessary to cite all of the service 

information references that were 

included in the proposed AD, which 

include various AMMs and Temporary 

Revisions. No change to the final rule is 

necessary in this regard. 

Explanation of Changes To Clarify/

Revise the Final Rule 

We have made the following 

additional changes to the final rule: 

• In the Summary section of the final 

rule, we have clarified the requirements 

for the repetitive measurement action. 

The Summary section of the proposed 

AD specifies repetitive measurement of 

the screw/nut play of the ‘‘outboard and 

center flap’’ jackscrews. However, the 

repetitive measurement action in 

paragraph (f) of the proposed AD 

specifies the location of the jackscrew 

on the ‘‘outboard flaps,’’ and paragraph 

(g) of the proposed AD specifies the 

‘‘inboard flap.’’ For this reason, we have 

revised the Summary of the final rule to 

specify measurement of the jackscrews 

on the ‘‘inboard and outboard flaps.’’

The exact location of the affected 

jackscrews is specified in paragraphs (f) 

through (h) of the final rule. 

• Although paragraphs (c) and (e) of 

the proposed AD specify a 

reconditioned jackscrew having P/N 

5318–1, we have revised those 

paragraphs in the final rule to clarify 

that the correct P/N of a reconditioned 

jackscrew is P/N 5318–1 Amdt A. 

• Although paragraphs (c)(1) and 

(e)(1) and Note 2 of the proposed AD 

did not include the date of the 

referenced service bulletin, we have 

added the date (September 16, 1999) in 

those paragraphs in the final rule.

• In the proposed AD, paragraph 

(c)(2) specifies that the jackscrew is 

located on the inboard flap in the 

‘‘inboard’’ position, and paragraph (e)(2) 

specifies the location of the jackscrew in 

the ‘‘outboard’’ position. However, 

because the jackscrew could be located 

in either the inboard or outboard 

position, we have determined that the 

requirements in those paragraphs are 

unnecessary and should be deleted. In 

light of this, we have revised the final 

rule and renumbered the subparagraphs 

accordingly. 

• In paragraph (d) of the final rule, we 

have clarified the location of the middle 

jackscrew by specifying that the 

jackscrew is located on the inboard flap 

and in the outboard position. We have 

also clarified the location of the 

jackscrew in paragraph (e) of the final 

rule. 

Conclusion 

After careful review of the available 

data, including the comments 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 

This AD is considered to be interim 

action. The manufacturer has advised 

that it is currently developing a 

modification that will positively address 

the unsafe condition which is the 

subject of this AD. Once this 

modification is developed, approved, 

and available, the FAA may consider 

additional rulemaking. 

Cost Impact 

There are approximately 45 airplanes 

of U.S. registry that will be affected by 

this AD. 

The costs of performing actions 

required by AD 99–14–07 and retained 

in this AD for Falcon 2000 series 

airplanes are described below. 

The repetitive operational test of the 

flap asymmetry detection system takes 

approximately 1 work hour per airplane 

to accomplish, at an average labor rate 

of $60 per work hour. Based on these 

figures, the cost impact of the repetitive 

operational test on U.S. operators is 

estimated to be $2,700, or $60 per 

airplane, per test cycle. 

71454 Federal Register / Vol. 67, No. 231 / Monday, December 2, 2002 / Rules and Regulations 

The measurement of the screw/nut 

play in the flap jackscrews takes 

approximately 8 work hours per 

airplane to accomplish, at an average 

labor rate of $60 per work hour. Based 

on these figures, the cost impact of the 

measurement on U.S. operators is 

estimated to be $21,600, or $480 per 

airplane, per measurement cycle. 

The repetitive replacement of 

jackscrews takes approximately 8 work 

hours per airplane to accomplish, at an 

average labor rate of $60 per work hour. 

New jackscrews cost approximately 

$21,200 per airplane. However, the AD 

permits a one-time reconditioning and 

re-use of jackscrews, which could 

reduce the cost of parts by 50%. Based 

on these figures, the cost impact of 

replacement of jackscrews on U.S. 

operators is estimated to be between 

$498,600 and $975,600, or between 

$11,080 and $21,680 per airplane, per 

replacement cycle. 

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 39–11218 (64 FR 

36561, July 7, 1999), and by adding a 

new airworthiness directive (AD), 

amendment 39–12963, to read as 

follows:

2002–23–19 Dassault Aviation (Formerly 

Avions Marcel Dassault-Breguet 

Aviation (AMD/BA)): Amendment 39–

12963; Docket 2000–NM–417–AD. 

Supersedes AD 99–14–07, Amendment 

39–11218.

Applicability: All Model Falcon 2000 series 

airplanes, certificated in any category.

Note 1: This AD applies to each airplane 

identified in the preceding applicability 

provision, regardless of whether it has been 

modified, altered, or repaired in the area 

subject to the requirements of this AD. For 

airplanes that have been modified, altered, or 

repaired so that the performance of the 

requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (i)(1) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it.

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent jamming of the flap jackscrews 

during the approach to landing, which could 

result in the inability to move the flaps or an 

asymmetric flap condition, and consequent 

reduced controllability of the airplane, 

accomplish the following: 

Repetitive Operational Test 

(a) Within 5 flight cycles after August 11, 

1999 (the effective date of AD 99–14–07, 

amendment 39–11218): Perform an 

operational test of the flap asymmetry 

detection system to ensure that the system is 

functioning correctly, in accordance with the 

procedures specified in Dassault Falcon 2000 

Airplane Maintenance Manual (AMM) 27–

502, dated November 1995. Prior to further 

flight, repair any discrepancy detected, in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate; or the 

Direction Ge ́ne ́rale de l’Aviation Civile (or its 

delegated agent). Repeat the operational test 

thereafter at intervals not to exceed 330 flight 

hours or 7 months, whichever occurs first. 

Repetitive Replacement 

(b) Prior to the accumulation of 1,000 total 

flight cycles on the inboard jackscrew located 

on the inboard flap in the inboard position, 

or within 25 flight cycles after August 11, 

1999, whichever occurs later: Replace each 

jackscrew having part number (P/N) 5318–1 

or 5318–1 Amdt A, which is located on the 

inboard flap in the inboard position, in 

accordance with Dassault Falcon 2000 AMM 

27–510, dated November 1995. The 

replacement jackscrew may be new or may 

have been reconditioned in accordance with 

paragraph (c) of this AD. Repeat the 

replacement of a jackscrew having P/N 5318–

1 or 5318–1 Amdt A thereafter at intervals 

not to exceed 1,000 flight cycles on the 

jackscrew located on the inboard flap in the 

inboard position. 

(c) A jackscrew having P/N 5318–1 and 

located on the inboard flap in the inboard 

position may be replaced by a reconditioned 

jackscrew having P/N 5318–1 Amdt A, 

provided that all of the conditions specified 

in paragraphs (c)(1) and (c)(2) of this AD are 

met. 

(1) The jackscrew has been reconditioned 

and reidentified as P/N 5318–1 Amdt A, in 

accordance with Dassault Service Bulletin 

AVIAC 5318–27–01, dated September 16, 

1999. 

(2) The jackscrew has been reconditioned 

only one time. 

(d) Prior to the accumulation of 2,200 total 

flight cycles on the middle jackscrew located 

on the inboard flap and in the outboard 

position, or within 25 flight cycles after 

August 11, 1999, whichever occurs later: 

Replace each jackscrew having P/N 5318–1 

or 5318–1 Amdt A on the inboard flap and 

in the outboard position, in accordance with 

Dassault Falcon 2000 AMM 27–510, dated 

November 1995. The replacement jackscrew 

may be new or may have been reconditioned 

in accordance with paragraph (e) of this AD. 

Repeat the replacement of a jackscrew having 

P/N 5318–1 or 5318–1 Amdt A thereafter at 

intervals not to exceed 2,200 flight cycles on 

the jackscrew located on the inboard flap and 

in the outboard position. 

(e) A jackscrew having P/N 5318–1 and 

located on the inboard flap and in the 

outboard position may be replaced by a 

reconditioned jackscrew having P/N 5318–1 

Amdt A, provided that all of the conditions 

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

this AD are met. 

(1) The jackscrew has been reconditioned 

and reidentified as P/N 5318–1 Amdt A, in 

accordance with Dassault Service Bulletin 

AVIAC 5318–27–01, dated September 16, 

1999. 

(2) The jackscrew has been reconditioned 

only one time. 

Repetitive Measurements 

(f) Prior to the accumulation of 1,000 total 

flight cycles on the outboard jackscrews 

Federal Register / Vol. 67, No. 231 / Monday, December 2, 2002 / Rules and Regulations 71455

located on the outboard flaps, or within 25 

flight cycles after August 11, 1999, whichever 

occurs later: Measure the screw/nut play of 

the jackscrews having P/N 1–5319–1 or 1–

5319–1 Amdt A (on the left wing) and P/N 

2–5319–1 or 2–5319–1 Amdt A (on the right 

wing) on the outboard flaps, in accordance 

with the procedures specified in Dassault 

Falcon 2000 AMM Temporary Revision (TR) 

27–504, dated October 1998.

Note 2: Jackscrews having P/N 1–5319–1 or 

2–5319–1 may be reconditioned in 

accordance with Dassault Service Bulletin 

AVIAC 5319–27–01, dated September 16, 

1999. These jackscrews may be reconditioned 

and reused more than one time.

(1) If the initial measurement is equal to or 

less than 0.014 inch: Repeat the measurement 

thereafter at intervals not to exceed 330 flight 

hours or 7 months, whichever occurs first. If 

any repetitive measurement detects a nut/

screw play greater than 0.014 inch, perform 

the actions required by paragraph (f)(2) of 

this AD. 

(2) If the initial measurement is greater 

than 0.014 inch: Perform the actions required 

by paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.

(i) Prior to further flight, replace the 

jackscrew with a new or reconditioned 

jackscrew, in accordance with Dassault 

Falcon 2000 AMM 27–510, dated November 

1995. 

(ii) Prior to the accumulation of 1,000 total 

flight cycles on the new or reconditioned 

jackscrew, perform a follow-on measurement 

of the screw/nut play in accordance with the 

procedures specified in Dassault Falcon 2000 

AMM TR 27–504, dated October 1998. 

(iii) If any follow-on measurement required 

by paragraph (f)(2)(ii) of this AD detects a 

nut/screw play equal to or less than 0.014 

inch, perform the actions required by 

paragraph (f)(1) of this AD. If any follow-on 

measurement required by paragraph (f)(2)(ii) 

of this AD detects a nut/screw play greater 

than 0.014 inch, perform the actions required 

by paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. 

(g) Prior to the accumulation of 750 total 

flight cycles on the jackscrew located on the 

inboard flap in the inboard position, or 

within 25 flight cycles after the effective date 

of this AD, whichever occurs later: Measure 

the screw/nut play of the jackscrew having P/

N 5318–1 or 1–5318–1 Amdt A, which is 

located on the inboard flap in the inboard 

position, to detect discrepancies, in 

accordance with the procedures specified in 

Dassault Falcon 2000 AMM TR 27–504, 

dated October 1998. If the measurement is 

greater than 0.014 inch, prior to further flight, 

replace the discrepant jackscrew with a new 

or reconditioned jackscrew, in accordance 

with Dassault Falcon 2000 AMM 27–510, 

dated November 1995. 

(h) Prior to the accumulation of 1,000 total 

flight cycles on the jackscrew located on the 

inboard flap in the outboard position, or 

within 25 flight cycles after the effective date 

of this AD, whichever occurs later: Measure 

the screw/nut play of the jackscrew having P/

N 5318–1 or 5318–1 Amdt A, which is 

located on the inboard flap in the outboard 

position, in accordance with the procedures 

specified in Dassault Falcon 2000 AMM TR 

27–504, dated October 1998. 

(1) If the initial measurement is equal to or 

less than 0.014 inch: Repeat the 

measurements thereafter at intervals not to 

exceed 330 flight hours or 7 months, 

whichever occurs first. If repetitive 

measurement detects a nut/screw play greater 

than 0.014 inch, perform the actions required 

by paragraph (h)(2) of this AD. 

(2) If the initial measurement is greater 

than 0.014 inch: Perform the actions required 

by paragraphs (h)(2)(i) and (h)(2)(ii) of this 

AD. 

(i) Prior to further flight, replace the 

jackscrew with a new or reconditioned 

jackscrew, in accordance with Dassault 

Falcon 2000 AMM 27–510, dated November 

1995. 

(ii) Prior to the accumulation of 1,000 total 

flight cycles on the new or reconditioned 

jackscrew, perform a follow-on measurement 

of the screw/nut play in accordance with the 

procedures specified in Dassault Falcon 2000 

AMM TR 27–504, dated October 1998. 

(iii) If any follow-on measurement required 

by paragraph (h)(2)(ii) of this AD detects a 

nut/screw play equal to or less than 0.014 

inch, perform the actions required by 

paragraph (h)(1) of this AD. If any follow-on 

measurement required by paragraph (h)(2)(ii) 

of this AD detects a nut/screw play greater 

than 0.014 inch, perform the actions required 

by paragraphs (h)(2)(i) and (h)(2)(ii) of this 

AD. 

Alternative Methods of Compliance 

(i)(1) An alternative method of compliance 

or adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, 

International Branch, ANM–116. Operators 

shall submit their requests through an 

appropriate FAA Principal Maintenance 

Inspector, who may add comments and then 

send it to the Manager, International Branch, 

ANM–116. 

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

99–14–07, amendment 39–11218, are not 

considered to be approved as alternative 

methods of compliance with this AD. 

Special Flight Permits 

(j) Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the requirements of this AD 

can be accomplished. 

Incorporation by Reference 

(k) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Dassault Falcon 2000 Airplane Maintenance 

Manual Temporary Revision 27–504, dated 

October 1998. 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 3: The subject of this AD is addressed 

in French airworthiness directive 1999–038–

008(B) R1, dated September 20, 2000.

Effective Date 

(l) This amendment becomes effective on 

January 6, 2003.

Issued in Renton, Washington, on 

November 19, 2002. 

Ali Bahrami, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 02–30025 Filed 11–29–02; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–40–AD; Amendment 

39–12969; AD 2002–24–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 and B4 Series Airplanes; A300 

B4–600, B4–600R, and F4–600R 

(Collectively Called A300–600) Series 

Airplanes; and Model A310 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) that is 

applicable to all Airbus Model A300 B2 

and B4 series airplanes; A300 B4–600, 

B4–600R, and F4–600R (collectively 

called A300–600) series airplanes; and 

Model A310 series airplanes. This 

amendment requires revising the 

Airplane Flight Manual to advise the 

flightcrew to don oxygen masks as a first 

and immediate step when the cabin 

altitude warning horn sounds. This 

action is necessary to prevent 

incapacitation of the flightcrew due to 

lack of oxygen, which could result in 

loss of control of the airplane. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective January 6, 2003.

ADDRESSES: Information pertaining to 

this AD may be examined at the Federal 

Aviation Administration (FAA), 

Transport Airplane Directorate, Rules 

Docket, 1601 Lind Avenue, SW., 

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to