[Federal Register Volume 69, Number 133 (Tuesday, July 13, 2004)]
[Rules and Regulations]
[Pages 41928-41930]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-15513]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-339-AD; Amendment 39-13727; AD 2004-14-18]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-102, -103, and -
106 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Bombardier Model DHC-8-102, -103, and -106 
airplanes, that requires repetitive detailed inspections of the left 
and right aileron tab actuator arm channels for cracking, and 
corrective actions if necessary. This proposal also provides an 
optional terminating action for the repetitive inspections. This action 
is necessary to prevent increased roll forces due to cracking of the 
left and right aileron tab actuator arms, which could be interpreted by 
the pilot as a flight control problem and might lead to loss of control 
of the airplane. This action is intended to address the identified 
unsafe condition.

DATES: Effective August 17, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 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 New York Aircraft Certification 
Office, 1600 Stewart Avenue, suite 410, Westbury, New York; or at the 
National Archives and Records Administration (NARA). For information on 
the availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Richard Beckwith, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office (ACO), 1600 Stewart

[[Page 41929]]

Ave., Westbury, NY 11590; telephone (516) 228-7306; 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, and -106 airplanes was published in the Federal Register on 
May 5, 2004 (69 FR 25041). That action proposed repetitive detailed 
inspections of the left and right aileron tab actuator arm channels for 
cracking, and corrective actions if necessary. That action also 
proposed an optional terminating action for the repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments have been submitted on the 
proposed AD or on the determination of the cost to the public.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule as proposed.

Cost Impact

    We estimate that 30 airplanes of U.S. registry will be affected by 
this AD, that it will take approximately 1 work hour per airplane to 
accomplish each required repetitive 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 $1,950, or $65 
per airplane, per inspection.
    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

0
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

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-14-18 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-13727. Docket 2002-NM-339-AD.

    Applicability: Model DHC-8-102, -103, and -106 airplanes; serial 
numbers 3 through 119 inclusive; without Bombardier Modification 8/
0864 incorporated; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent increased roll forces due to cracking of the left and 
right aileron tab actuator arm channels, which could be interpreted 
by the pilot as a flight control problem and might lead to loss of 
control of the airplane, accomplish the following:

Inspection and Corrective Actions

    (a) Within 500 flight hours after the effective date of this AD, 
perform a detailed inspection of the left and right aileron tab 
actuator arm channels for cracking, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 8-57-07, 
Revision ``F,'' dated March 27, 2002.

    Note 1: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

    (1) If no cracked actuator arm channel is found, repeat the 
inspection at intervals not to exceed 500 flight hours, until 
paragraph (a)(2) or (b) of this AD has been accomplished.
    (2) If any cracked actuator arm channel is found, prior to 
further flight, accomplish paragraph (a)(2)(i) or (a)(2)(ii) of this 
AD. Accomplishment of paragraph (a)(2)(i) or (a)(2)(ii) terminates 
the repetitive inspections required by paragraph (a)(1) of this AD 
for the repaired or replaced aileron tab only.
    (i) Replace the actuator arm channel with a new actuator arm 
channel; install a reinforcing angle on the new actuator arm 
channel; and replace the balance weight arm with a new balance 
weight arm; in accordance with Part A of the Accomplishment 
Instructions of the service bulletin.
    (ii) Replace the aileron tab with a new, improved aileron tab in 
accordance with Part C of the Accomplishment Instructions of the 
service bulletin.

Optional Terminating Action

    (b) Reinforcement of both actuator arm channels with reinforcing 
angles and installation of new balance weight arms in accordance 
with Part B of the Accomplishment Instructions of Bombardier Service 
Bulletin 8-57-07, Revision ``F,'' dated March 27, 2002; or 
replacement of the aileron tabs with new, improved tabs in 
accordance with Part C of the Accomplishment Instructions of that 
service bulletin; constitutes terminating action for the repetitive 
inspections required by paragraph (a)(1) of this AD.

Part Installation

    (c) As of the effective date of this AD, no person may install 
any actuator arm channel or any aileron tab on any airplane except 
in accordance with paragraph (a)(2) or (b) of this AD.

Alternative Methods of Compliance

    (d) In accordance with 14 CFR 39.19, the Manager, New York 
Aircraft Certification Office (ACO), FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (e) The actions shall be done in accordance with Bombardier 
Service Bulletin 8-57-07, Revision ``F,'' dated March 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 Bombardier, Inc., Bombardier 
Regional Aircraft Division, 123 Garratt Boulevard, Downsview, 
Ontario M3K 1Y5, Canada. This information may be examined at the 
Federal

[[Page 41930]]

Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the New 
York Aircraft Certification Office, 1600 Stewart Avenue, suite 410, 
Westbury, New York; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Note 2: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2002-29, dated May 22, 2002.

Effective Date

    (f) This amendment becomes effective on August 17, 2004.

    Issued in Renton, Washington, on June 30, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-15513 Filed 7-12-04; 8:45 am]
BILLING CODE 4910-13-P