6546 Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 

comments and then send it to the Manager, 

Seattle ACO.

Note 3: 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 

(l) 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 

(m) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing Service Bulletin 747–57A2314, 

Revision 1, dated January 9, 2003. 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, 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 

(n) This amendment becomes effective on 

March 17, 2004.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2571 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–79–AD; Amendment 

39–13472; AD 2004–03–28] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315 Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Bombardier Model 

DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes, that 

requires a one-time inspection to 

determine the serial numbers of the 

elevator and aileron servos of the drive 

assemblies of the automatic flight 

control system, and follow-on corrective 

actions if necessary. This action is 

necessary to prevent separation of the 

screws from the autopilot clutch 

assembly of the SM–300 servo, which 

could result in uncommanded 

engagement of the autopilot servo and 

consequent reduced controllability of 

the airplane. 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 Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 

1Y5, Canada. 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, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at 

the FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Westbury, New York; or at the 

Office of the Federal Register, 800 North 

Capitol Street, NW., suite 700, 

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ezra 

Sasson, Aerospace Engineer, Systems 

and Flight Test Branch, ANE–172, FAA, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, Westbury, New 

York 11581; telephone (516) 228–7300; 

fax (516) 794–5531.

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 Bombardier 

Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315 airplanes 

was published in the Federal Register

on December 11, 2003 (68 FR 69057). 

That action proposed to require a onetime inspection to determine the serial 

numbers of the elevator and aileron 

servos of the drive assemblies of the 

automatic flight control system, and 

follow-on corrective actions 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 

We estimate that 200 airplanes of U.S. 

registry will be affected by this AD. It 

will take approximately 1 work hour per 

airplane to accomplish the inspection, 

at an average labor rate of $65 per work 

hour. Based on these figures, the cost 

impact of the inspection on U.S. 

operators is estimated to be $13,000, or 

$65 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (1) is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 

‘‘significant rule’’ under DOT 

Regulatory Policies and Procedures (44 

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

will not have a significant economic 

impact, positive or negative, on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

Federal Register / Vol. 69, No. 28 / Wednesday, February 11, 2004 / Rules and Regulations 6547

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:

2004–03–28 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–13472. 

Docket 2002–NM–79–AD.

Applicability: Model DHC–8–102, –103, 

–106, –201, –202, –301, –311, and –315 

airplanes; serial numbers 003 through 580 

inclusive; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent separation of the screws in the 

autopilot clutch assembly of the SM–300 

servo, which could result in uncommanded 

engagement of the autopilot servo and 

consequent reduced controllability of the 

airplane, accomplish the following: 

One-Time Inspection/Follow-on Corrective 

Action, if Necessary 

(a) Within 12 months after the effective 

date of this AD: Do a general visual 

inspection to determine the serial numbers of 

the elevator and aileron servo drive 

assemblies of the automatic flight control 

system per paragraphs III.1. and III.2. of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A8–22–18, Revision 

‘B’, dated November 19, 2001.

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance unless otherwise specified. 

A mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight, or droplight and may require 

removal or opening of access panels or doors. 

Stands, ladders, or platforms may be required 

to gain proximity to the area being checked.’’

(1) If any elevator or aileron servo, part 

number (P/N) 7002260–922, or any aileron 

servo, P/N 7002260–923, with serial numbers 

4826 through 5935 inclusive, is found: Before 

further flight, do all the follow-on actions per 

paragraphs III.3. and III.4. of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A8–22–18, Revision 

‘‘B’’, dated November 19, 2001; and per 

paragraphs 3.A. through 3.F. of the 

Honeywell Accomplishment Instructions 

specified on pages 14 through 17 of the 

Bombardier service bulletin. 

(2) If no serial number specified in 

paragraph (a)(1) of this AD is found, no 

further action is required by this paragraph. 

Part Installation 

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

person may install an elevator or aileron 

servo, P/N 7002260–922, or an aileron servo, 

P/N 7002260–923, with serial numbers 4826 

through 5935 inclusive, on any airplane.

Note 2: Although Bombardier Alert Service 

Bulletin A8–22–18, Revision ‘‘B’’, dated 

November 19, 2001, specifies 

accomplishment of concurrent requirements, 

this AD does not include those requirements.

Alternative Methods of Compliance 

(c) In accordance with 14 CFR 39.19, the 

Manager, New York Aircraft Certification 

Office, FAA, is authorized to approve 

alternative methods of compliance for this 

AD. 

Incorporation by Reference 

(d) The actions shall be done in accordance 

with Bombardier Alert Service Bulletin A8–

22–18, Revision ‘B’, dated November 19, 

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 Bombardier Regional Aircraft Division, 

123 Garratt Boulevard, Downsview, Ontario 

M3K 1Y5, Canada. Copies may be inspected 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the FAA, New York 

Aircraft Certification Office, 1600 Stewart 

Avenue, Westbury, New York; 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 Canadian airworthiness directive CF–

2001–40, dated November 9, 2001.

Effective Date 

(e) 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. 04–2681 Filed 2–11–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–284–AD; Amendment 

39–13469; AD 2004–03–25] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 and A340–200 and –300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Airbus Model 

A330 and A340–200 and –300 series 

airplanes, that requires repetitive 

inspections for proper installation of the 

parachute pins located in the escape 

slides/rafts at the door 3 Type I 

emergency exits on the left and right 

sides of the airplane; a one-time 

inspection of the associated electrical 

harnesses for the escape slides/rafts for 

proper routing and installation; and 

corrective actions if necessary. This AD 

also requires adjustment of the speed 

lacing for the soft covers of the escape 

slides/rafts, which will terminate the 

repetitive inspections. This action is 

necessary to prevent failure of the 

escape slides/rafts to deploy correctly at 

door 3 Type I emergency exits, which 

could result in the escape slides/rafts 

being unusable during an emergency 

evacuation, and consequent injury to 

passengers or crew members. 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 Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

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: 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: 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 Airbus 

Model A330 and A340–200 and –300 

series airplanes was published in the 

Federal Register on December 5, 2003 

(68 FR 67984). That action proposed to 

require repetitive inspections for proper 

installation of the parachute pins 

located in the escape slides/rafts at the 

door 3 Type I emergency exits on the 

left and right sides of the airplane; a 

one-time inspection of the associated 

electrical harnesses for the escape 

slides/rafts for proper routing and