6532 Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 

ACTION: Final rule; correction.

SUMMARY: This document makes a 

correction to the correction of the final 

rule published in the Federal Register

on June 25, 2003. The first correction 

changed assigned amendment numbers. 

This action makes further corrections to 

assigned amendment numbers.

EFFECTIVE DATE: This correction is 

effective on February 11, 2004.

FOR FURTHER INFORMATION CONTACT:

Mike Dosert, telephone (425) 227–2132.

Correction

■ In correction to the final rule FR Doc. 

03–16001, published on June 25, 2003 

(68 FR 37735), make the following 

corrections:

■ 1. On page 37735, at the bottom of 

column 2, in the heading section, 

beginning on line 4, correct 

‘‘Amendment. Nos. 21–83, 91–272, 121–

285, 125–40, 129–35; Special Federal 

Aviation Regulation No. 88’’ to read 

‘‘Amendment. Nos. 21–83, 91–277, 121–

295, 125–40, 129–35; Special Federal 

Aviation Regulation No. 88’’.

Donald P. Byrne, 

Assistant Chief Counsel for Regulations.

[FR Doc. 04–2878 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Parts 25, 91, 121, 125, and 135 

[Docket No. FAA–2000–7909; Amdt. Nos. 

25–110, 91–279, 121–301, 125–43, 135–90] 

RIN 2120–AG91 

Improved Flammability Standards for 

Thermal/Acoustic Insulation Materials 

Used in Transport Category Airplanes; 

Correction

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; correction.

SUMMARY: This document makes a 

correction to the amendment numbers 

in the final rule published in the 

Federal Register on July 31, 2003. That 

rule adopted upgraded flammability 

standards for thermal and acoustic 

insulation materials used in transport 

category airplanes.

EFFECTIVE DATE: This correction is 

effective on February 11, 2004.

FOR FURTHER INFORMATION CONTACT: Jeff 

Gardlin, (425) 227–2136. 

Correction

■ In the final rule FR Doc. 03–18612 

published on July 31, 2003, (68 FR 

45046), make the following corrections:

■ 1. On page 45046, in column 1, in the 

heading section, beginning on line 4 

correct ‘‘Amdt. Nos. 25–110, 91–275, 

121–289, 125–43, 135–85’’ to read 

‘‘Amdt. Nos. 25–110, 91–279, 121–301, 

125–43, 135–90 ’’.

Issued in Washington, DC, on January 30, 

2004. 

Donald P. Byrne, 

Assistant Chief Counsel for Regulations.

[FR Doc. 04–2875 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–213–AD; Amendment 

39–13465; AD 2004–03–21] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model 717–200 Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain McDonnell 

Douglas Model 717–200 airplanes, that 

requires inspection of the inboard ends 

of the outer skin panels of the horizontal 

stabilizer at Station Xh=±7.234 for 

material defects, and corrective action, 

if necessary. This action is necessary to 

detect material defects in the inboard 

ends of the outer skin panels of the 

horizontal stabilizer, which could lead 

to cracks and an associated loss of 

strength in the attachments, and 

consequent reduced structural integrity 

of the horizontal stabilizer. This action 

is intended to address the identified 

unsafe condition.

DATES: Effective March 17, 2004. 

The incorporation by reference of a 

certain publication 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 Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 

90846, Attention: Data and Service 

Management, Dept. C1–L5A (D800–

0024). 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 FAA, Los Angeles 

Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, 

California; or at the Office of the Federal 

Register, 800 North Capitol Street, NW., 

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Maureen Moreland, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5238; fax (562) 

627–5210.

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 McDonnell 

Douglas Model 717–200 airplanes was 

published in the Federal Register on 

September 18, 2003 (68 FR 54690). That 

action proposed to require inspection of 

the inboard ends of the outer skin 

panels of the horizontal stabilizer at 

Station Xh=±7.234 for material defects, 

and corrective action, if necessary. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

The FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

There are approximately 56 airplanes 

of the affected design in the worldwide 

fleet. The FAA estimates that 41 

airplanes of U.S. registry will be affected 

by this AD, that it will take 

approximately 4 work hours per 

airplane to accomplish the required 

inspection, and that the average labor 

rate is $65 per work hour. Based on 

these figures, the cost impact of the AD 

on U.S. operators is estimated to be 

$10,660, or $260 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6533

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Manufacturer warranty remedies may be 

available for labor costs associated with 

this proposed AD. As a result, the costs 

attributable to the proposed AD may be 

less than stated above. 

Regulatory Impact 

The regulations adopted herein will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (1) is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 

‘‘significant rule’’ under DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979); and (3) 

will not have a significant economic 

impact, positive or negative, on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (14 CFR part 39) as follows:

PART 39—AIRWORTHINESS 

DIRECTIVES

■ 1. The authority citation for part 39 

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

■ 2. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–03–21 McDonnell Douglas:

Amendment 39–13465. Docket 2002–

NM–213–AD.

Applicability: Model 717–200 airplanes, as 

listed in Boeing Service Bulletin 717–55–

0005, dated June 27, 2002; certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect material defects in the inboard 

ends of the outer skin panels of the 

horizontal stabilizer at Station Xh=±7.234, 

which could lead to cracks and an associated 

loss of strength in the attachments, and 

consequent reduced structural integrity of the 

horizontal stabilizer, accomplish the 

following: 

Inspection 

(a) Prior to the accumulation of 10,000 total 

flight cycles, or within 15 months after the 

effective date of this AD, whichever occurs 

later, do an ultrasonic inspection of the 

inboard ends of the outer skin panels of the 

horizontal stabilizer at Station Xh=±7.234 for 

material defects, per the Accomplishment 

Instructions of Boeing Service Bulletin 717–

55–0005, dated June 27, 2002. 

Corrective Action 

(b) If any defects are found during the 

inspection required by paragraph (a) of this 

AD, and the service bulletin specifies 

contacting Boeing for appropriate action: 

Before further flight, repair per a method 

approved by the Manager, Los Angeles 

Aircraft Certification Office (ACO), FAA; 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, Los Angeles ACO, to make such 

findings. For a repair method to be approved, 

as required by this paragraph, the approval 

letter must specifically refer to this AD. 

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, Los Angeles ACO, FAA, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(d) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing Service Bulletin 717–55–0005, dated 

June 27, 2002. This incorporation by 

reference was approved by the Director of the 

Federal Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1–L5A (D800–0024). Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California; or at the 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, Washington, 

DC. 

Effective Date 

(e) This amendment becomes effective on 

March 17, 2004.

Issued in Renton, Washington, on January 

30, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2581 Filed 2–10–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–233–AD; Amendment 

39–13466; AD 2004–03–22] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Falcon 2000 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 2000 series airplanes, that 

requires modification of the forward ribs 

of the left and right engine pylons to 

plug holes left open during production. 

This action is necessary to prevent fuel 

leakage into a ‘‘hot’’ section of the 

engine, and consequent propagation of 

an uncontained engine fire. 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, 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 

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 2000 series airplanes was