71098 Federal Register / Vol. 67, No. 230 / Friday, November 29, 2002 / Rules and Regulations 

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 a new airworthiness directive to 

read as follows:

2002–23–04 Eurocopter France:

Amendment 39–12948. Docket No. 

2001–SW–34–AD.

Applicability: Model SA–365N, SA–365N1, 

AS–365N2, and AS 365 N3 helicopters, with 

MOD 0753B31 installed, certificated in any 

category.

Note 1: This AD applies to each helicopter 

identified in the preceding applicability 

provision, regardless of whether it has been 

otherwise modified, altered, or repaired in 

the area subject to the requirements of this 

AD. For helicopters 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 (b) 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 failure of the 9-degree frame 

(frame) due to a crack at the latch support, 

loss of a passenger door, damage to the rotor 

system, and subsequent loss of control of the 

helicopter, accomplish the following: 

(a) Within 50 hours time-in-service, inspect 

each frame by measuring the edge distance at 

the two 5.2 mm (0.205 inch) diameter 

attachment holes for the latch support for the 

passenger door in accordance with the 

Accomplishment Instructions, paragraph 

2.B.1., of Eurocopter France AS 365 Alert 

Service Bulletin 53.00.42, dated January 31, 

2001 (ASB). Inspect the area around the 

attachment holes for a crack. 

(1) If the edge distance of both attachment 

holes is equal to or more than 8 mm (0.315 

inch) and no crack is present, no action is 

required by this AD. 

(2) If the edge distance is less than 8 mm 

and no crack is present, before further flight, 

install a reinforcing plate in accordance with 

the Accomplishment Instructions paragraph 

2.B.2. of the ASB. Accomplishing the 

requirements of paragraph 2.B.2. of the ASB 

constitutes terminating action for the 

requirements of this AD. 

(3) If there is a crack, before further flight, 

stop-drill the crack with a 3-millimeter 

diameter hole and repair the frame in 

accordance with the Accomplishment 

Instructions, paragraph 2.B.3., of the ASB. 

Accomplishing the requirements of 

paragraph 2.B.3. of the ASB constitutes 

terminating action for the requirements of 

this AD. 

(b) 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, Regulations 

Group, Rotorcraft Directorate, FAA. 

Operators shall submit their requests through 

an FAA Principal Maintenance Inspector, 

who may concur or comment and then send 

it to the Manager, Regulations Group.

Note 2: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Regulations Group.

(c) Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the helicopter to a location where 

the requirements of this AD can be 

accomplished. 

(d) The inspection and repair shall be done 

in accordance with the Accomplishment 

Instructions of Eurocopter France AS 365 

Alert Service Bulletin 53.00.42, dated 

January 31, 2001. 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 American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, Texas 75053–4005, telephone (972) 

641–3460, fax (972) 641–3527. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas; or at the 

Office of the Federal Register, 800 North 

Capitol Street, NW., Suite 700, Washington, 

DC. 

(e) This amendment becomes effective on 

January 3, 2003.

Note 3: The subject of this AD is addressed 

in Direction Generale De L’Aviation Civile 

(France) AD No. 2001–060–052(A), dated 

February 21, 2001.

Issued in Fort Worth, Texas, on November 

6, 2002. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service.

[FR Doc. 02–29155 Filed 11–27–02; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NM–418–AD; Amendment 

39–12964; AD 2002–23–20] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Falcon 900EX and Mystere 

Falcon 900 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 and Mystere Falcon 900 

series airplanes, that 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 also requires revision of the 

Airplane Flight Manual. 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 3, 2003. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of January 3, 

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., 

Federal Register / Vol. 67, No. 230 / Friday, November 29, 2002 / Rules and Regulations 71099

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 and Mystere 

Falcon 900 series airplanes was 

published in the Federal Register on 

February 15, 2002 (67 FR 7097). That 

action proposed to continue to require 

the following actions, which are 

currently required by AD 99–14–07, 

amendment 39–11218 (64 FR 36561, 

July 7, 1999), for certain Model Falcon 

900EX and Mystere Falcon 900 series 

airplanes: 

• 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. 

The action also proposed to require 

revision of the Airplane Flight Manual 

(AFM). 

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 proposed AD. In order 

to accomplish the requirements of the 

proposed AD, it is necessary to cite all 

of the service information references 

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 the Final 

Rule 

We have made the following changes 

to the final rule: 

• In the Summary section of the final 

rule, we have clarified the requirements 

for the repetitive replacement action. 

Although the Summary section of the 

proposed AD specifies repetitive 

replacement of the inboard flap 

jackscrews ‘‘on the inboard,’’ we have 

deleted the term ‘‘on the inboard’’ in 

that section of the final rule because the 

replacement action is also required for 

the inboard flap jackscrews located in 

the outboard position. The exact 

location of the affected jackscrews is 

specified in paragraphs (b) 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), (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.

• Paragraph (i) of the proposed AD 

incorrectly specifies revising the 

‘‘Limitations’’ Section of the FAAapproved AFM. However, we have 

revised the final rule to specify revising 

the ‘‘Abnormal Procedures’’ Section of 

the AFM, as cited in French 

airworthiness directive 1999–082–

024(B) R2, dated September 20, 2000. 

• We have determined that NOTE 3 

in the proposed AD, which specifies a 

change to the general revisions of the 

AFM, is no longer necessary. We have 

revised the final rule and renumbered 

the notes accordingly. 

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. 

Cost Impact 

There are approximately 28 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 Model Falcon 900EX and 

Mystere Falcon 900 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 $1,680, or $60 per 

airplane, per test cycle. 

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 

71100 Federal Register / Vol. 67, No. 230 / Friday, November 29, 2002 / Rules and Regulations 

estimated to be $13,400, 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 

$310,240 and $607,040, or between 

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

replacement cycle. 

The revision of the AFM 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 AFM 

revision on U.S. operators is $1,680, or 

$60 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 

adding the following new airworthiness 

directive:

2002–23–20 Dassault Aviation (Formerly 

Avions Marcel Dassault-Breguet 

Aviation (AMD/BA)): Amendment 39–

12964. Docket 2000-NM–418–AD.

Applicability: Model Falcon 900EX, serial 

numbers 04 and up, and Mystere Falcon 900 

series airplanes, serial numbers 161 and up; 

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 (j)(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 900 

Airplane Maintenance Manual (AMM) 27–

502, dated January 1995; or Dassault Falcon 

900EX AMM 27–502, dated September 1996; 

as applicable. 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 Generale 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) 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 the 

procedures specified in Dassault Falcon 900 

AMM 27–521, dated December 1998; or 

Dassault Falcon 900EX AMM 27–510, dated 

September 1996; as applicable. The 

replacement jackscrew may be new or may 

have been reconditioned in accordance with 

paragraph (c) of this AD. Do the initial 

replacement at the earlier of the times 

specified in paragraphs (b)(1) and (b)(2) 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 

750 flight cycles on the jackscrew located on 

the inboard flap in the inboard position. 

(1) 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. 

(2) Prior to the accumulation of 750 total 

flight cycles on the inboard 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. 

(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 

the procedures specified in Dassault Falcon 

900 AMM 27–521, dated December 1998; or 

Dassault Falcon 900EX AMM 27–510, dated 

September 1996; as applicable. 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. 

Federal Register / Vol. 67, No. 230 / Friday, November 29, 2002 / Rules and Regulations 71101

(1) The jackscrew has been reconditioned 

and reidentified as P/N 5818–1 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 

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 900 AMM Temporary Revision (TR) 

27–514, dated February 1999; or Dassault 

Falcon 900EX AMM TR 27–514, dated 

February 1999; as applicable.

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 900 AMM 27–521, dated December 

1998; or Dassault Falcon 900EX AMM 27–

510, dated September 1996; as applicable. 

(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 900 

AMM TR 27–514, dated February 1999; or 

Dassault Falcon 900EX AMM TR 27–514, 

dated February 1999; as applicable. 

(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 (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 600 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 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 900 AMM TR 27–514, dated 

February 1999; or Dassault Falcon 900EX 

AMM TR 27–514, dated February 1999; as 

applicable. 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 

the applicable maintenance manual. 

(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 900 AMM TR 

27–514, dated February 1999; or Dassault 

Falcon 900EX AMM TR 27–514, dated 

February 1999; as applicable. 

(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 any 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 

discrepant jackscrew with a new or 

reconditioned jackscrew, in accordance with 

Dassault Falcon 900 AMM 27–521, dated 

December 1998; or Dassault Falcon 900EX 

AMM 27–510, dated September 1996; as 

applicable. 

(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 900 

AMM TR 27–514, dated February 1999; or 

Dassault Falcon 900EX AMM TR 27–514, 

dated February 1999; as applicable. 

(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. 

Airplane Flight Manual Revision 

(i) Within 7 days after the effective date of 

this AD: Revise the Abnormal Procedures 

Section of the FAA-approved Airplane Flight 

Manual (AFM) to include the following 

statement (this may be accomplished by 

inserting a copy of this AD in the AFM): 

‘‘In case of discrepancy between the 

control position and flap position indicator, 

do not change flap position control handle. 

Apply flight manual abnormal procedure 

‘Flight controls—system jamming or 

asymmetry’ for approach speed and landing 

distance.’’

Alternative Methods of Compliance 

(j)(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 

(k) 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 

(l) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Dassault Falcon 900 Airplane Maintenance 

Manual Temporary Revision 27–514, dated 

February 1999; or Dassault Falcon 900EX 

Airplane Maintenance Manual Temporary 

Revision 27–514, dated February 1999; 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 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 1999–082–

024(B) R2, dated September 20, 2000.

Effective Date 

(m) This amendment becomes effective on 

January 3, 2003.

Issued in Renton, Washington, on 

November 19, 2002. 

Vi L. Lipski, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 02–30024 Filed 11–27–02; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–CE–36–AD; Amendment 

39–12966; AD 2002–24–01] 

RIN 2120–AA64 

Airworthiness Directives; Britten 

Norman (Bembridge) Limited BN2A 

Mk. III Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.