[Federal Register Volume 68, Number 243 (Thursday, December 18, 2003)]
[Rules and Regulations]
[Pages 70434-70435]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31062]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-78-AD; Amendment 39-13386; AD 2003-25-03]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-400, -401, and -
402 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-8-400, -401, and -402 
airplanes, that requires a one-time inspection of the forward engine 
mount assemblies on the left and right engine nacelles for installation 
of pre-production engine mount assemblies, and follow-on corrective 
actions if necessary. This action is necessary to prevent failure of 
the forward engine mount, which could result in reduced structural 
integrity of the nacelle and engine support structure. This action is 
intended to address the identified unsafe condition.

DATES: Effective January 22, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 22, 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, New York Aircraft Certification 
Office, 10 Fifth Street, Third Floor, Valley Stream, New York; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Douglas G. Wagner, Aerospace Engineer, 
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft 
Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New 
York 11581; telephone (516) 256-7506; fax (516) 568-2716.

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-
400, -401, and -402 airplanes was published in the Federal Register on 
October 9, 2003 (68 FR 58287). That action proposed to require a one-
time inspection of the forward engine mount assemblies on the left and 
right engine nacelles for installation of pre-production engine mount 
assemblies, 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 11 airplanes of U.S. registry will be affected by 
this AD, that it will take approximately 2 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 $1,430, or $130 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

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:

2003-25-03 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 
39-13386. Docket 2002-NM-78-AD.

    Applicability: Model DHC-8-400, -401, and -402 airplanes; serial 
numbers 4005, 4006, 4008 through 4016 inclusive, 4018 through 4051 
inclusive, and 4053; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the forward engine mount, which could 
result in reduced structural integrity of the nacelle and engine 
support structure, accomplish the following:

[[Page 70435]]

Inspection

    (a) Within 100 flight cycles after the effective date of this 
AD: Do a general visual inspection of the forward engine mount 
assemblies on the left and right engine nacelles for installation of 
pre-production assemblies (determine the part number and 
configuration for each assembly), per the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A84-71-06, 
Revision ``A,'' dated December 5, 2001. If no pre-production engine 
mount assembly is installed, no further action is required by this 
AD.

    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.''

Follow-on Corrective Actions

    (b) If any pre-production engine mount assembly is installed, do 
all the applicable follow-on corrective actions (including 
repetitive detailed inspections for cracking, and rework or 
replacement of the pre-production engine mount assembly if 
necessary), per all the actions specified in the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A84-71-06, 
Revision ``A,'' dated December 5, 2001, at the applicable times 
specified in Paragraph I., Part D., ``Compliance,'' of the service 
bulletin. Any replacement due to cracking must be done before 
further flight.

    Note 2: 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.''

Optional Terminating Action for Follow-on Repetitive Inspections

    (c) Installation of production engine mount assemblies on all 
four forward engine mounts ends the repetitive inspection 
requirements of paragraph (b) of this AD.

Part Installation

    (d) As of the effective date of this AD, no person may install 
an engine mount assembly having a pre-production configuration and/
or part number 96042-07 on any airplane, unless the assembly has 
been reworked per Part B of the Accomplishment Instructions of 
Bombardier Alert Service Bulletin A84-71-06, Revision ``A,'' dated 
December 5, 2001.

Alternative Methods of Compliance

    (e) 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

    (f) Unless otherwise provided in this AD, the actions shall be 
done per Bombardier Alert Service Bulletin A84-71-06, Revision 
``A,'' dated December 5, 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, Inc., 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, 10 Fifth Street, Third Floor, Valley Stream, 
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-2002-07, dated January 21, 2002.

Effective Date

    (g) This amendment becomes effective on January 22, 2004.

    Issued in Renton, Washington, on December 5, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-31062 Filed 12-17-03; 8:45 am]
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