AD 2001-04-02

[Federal Register Volume 66, Number 35 (Wednesday, February 21, 2001)]
[Rules and Regulations]
[Pages 10960-10962]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-3851]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-102-AD; Amendment 39-12120; AD 2001-04-02]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model DHC-8-100, -200, and -
300 Series 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-8-100, -200, and -300 series 
airplanes, that requires inspection to determine the orientation of the 
Wiggins fuel couplers of the fuel tank vent line and scavenge line in 
the right wing at station 249, and follow-on corrective actions. This 
amendment is necessary to prevent contact between the nuts of the 
Wiggins fuel couplers and the stiffener on the access panel of the 
upper surface of the right wing, which could compromise the lightning 
protection of the fuel tank of the right wing in the event of a 
lightning strike, and could result in possible fuel tank explosion. 
This action is intended to address the identified unsafe condition.

DATES: Effective March 28, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 28, 2001.

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: Serge Napoleon, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New 
York 11581; telephone (516) 256-7512; 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-
100, -200, and -300 series airplanes was published in the Federal 
Register on November 7, 2000 (65 FR 66657). That action proposed to 
require inspection to determine the orientation of the Wiggins fuel 
couplers of the fuel tank vent line and scavenge line in the right wing 
at station 249, and follow-on corrective actions.

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

    The FAA estimates that 195 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the actions (inspection) specified in Part A of of Bombardier Alert 
Service Bulletin A8-28-32, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of these required actions 
on U.S. operators is estimated to be $11,700, or $60 per airplane.
    It will take approximately 2 work hours per airplane to accomplish 
the actions (rework) specified in Part B of the alert service bulletin, 
at an average labor rate of $60 per work hour. Based on these figures, 
the cost impact of these

[[Page 10961]]

required actions on U.S. operators is estimated to be $23,400, or $120 
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.


Sec. 39.13  [Amended]

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

2001-04-02  Bombardier, Inc. (Formerly de Havilland, Inc.): 
Amendment 39-12120. Docket 2000-NM-102-AD.

    Applicability: Model DHC-8-100, -200, and -300 series airplanes 
having serial numbers 003 through 540 inclusive; 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 (d) 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 contact between the nuts of the Wiggins fuel couplers 
and the stiffener on the access panel of the upper surface of the 
right wing, which could compromise the lightning protection of the 
fuel tank of the right wing in the event of a lightning strike, and 
could result in possible fuel tank explosion, accomplish the 
following:

General Visual or X-ray Inspection

    (a) Within 90 days after the effective date of this AD: Perform 
a one-time general visual or X-ray inspection to determine the 
orientation of the Wiggins fuel couplers of the fuel tank vent line 
and scavenge line in the right wing at station 249, in accordance 
with Part A of the Accomplishment Instructions of Bombardier Alert 
Service Bulletin A8-28-32, dated January 14, 2000.

    Note 2: 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 under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, 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.''

Action for Airplanes Having Correctly Oriented Fuel Couplers

    (b) For airplanes on which the orientation of all Wiggins fuel 
couplers is found to be correct, as specified in Bombardier Alert 
Service Bulletin A8-28-32, dated January 14, 2000: Within 5,000 
flight hours after the effective date of this AD, rework the 
stiffener on the access panel of the upper surface of the right wing 
in accordance with Part B of the Accomplishment Instructions of the 
alert service bulletin.

Actions for Airplanes Having an Incorrectly Oriented Fuel Coupler

    (c) For airplanes on which the orientation of any Wiggins fuel 
coupler is incorrect, as specified in Bombardier Alert Service 
Bulletin A8-28-32, dated January 14, 2000: Prior to further flight, 
remove the incorrectly oriented Wiggins fuel coupler, and perform a 
one-time detailed visual inspection to detect damage of the fuel 
coupler, in accordance with Part A of the Accomplishment 
Instructions of the alert service bulletin.

    Note 3: For the purposes of this AD, a detailed visual 
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 damage is found: Prior to further flight, reinstall 
the Wiggins fuel coupler in the correct orientation, as specified in 
the alert service bulletin, and rework the stiffener on the access 
panel of the upper surface of the right wing, in accordance with 
Part B of the Accomplishment Instructions of the alert service 
bulletin. No further action is required by this AD.
    (2) If any damage is found, prior to further flight, blend out 
the damage and perform a detailed visual inspection of the fuel 
coupler for cracks, in accordance with the alert service bulletin.
    (i) If no crack is found, and blending CAN be accomplished to 
meet the limits specified in the Accomplishment Instructions of the 
alert service bulletin: Prior to further flight, reinstall the 
Wiggins fuel coupler in the correct orientation, as specified in the 
alert service bulletin, and rework the stiffener on the access panel 
of the upper surface of the right wing, in accordance with Part B of 
the Accomplishment Instructions of the alert service bulletin. No 
further action is required by this AD.
    (ii) If any crack is found, or if blending CANNOT be 
accomplished to meet the limits specified in the Accomplishment 
Instructions of the alert service bulletin: Prior to further flight, 
replace the Wiggins fuel coupler with a new or serviceable coupler 
in the correct orientation, as specified in the alert service 
bulletin, and rework the stiffener on the access panel of the upper 
surface of the right wing, in accordance with Part B of the 
Accomplishment Instructions of the alert service bulletin. No 
further action is required by this AD.

Alternative Methods of Compliance

    (d) 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, New York Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, New York ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of

[[Page 10962]]

compliance with this AD, if any, may be obtained from the New York 
ACO.

Special Flight Permits

    (e) 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

    (f) The actions shall be done in accordance with Bombardier 
Alert Service Bulletin A8-28-32, dated January 14, 2000. 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 5: The subject of this AD is addressed in Canadian 
airworthiness directive CF-2000-05, dated February 28, 2000.

Effective Date

    (g) This amendment becomes effective on March 28, 2001.

    Issued in Renton, Washington, on February 9, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-3851 Filed 2-20-01; 8:45 am]
BILLING CODE 4910-13-U