[Federal Register Volume 62, Number 237 (Wednesday, December 10, 1997)]
[Rules and Regulations]
[Pages 65009-65011]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-32118]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-120-AD; Amendment 39-10238; AD 97-25-14]
RIN 2120-AA64
Airworthiness Directives; de Havilland 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 de Havilland Model DHC-8-100, -200, and -300
series airplanes, that requires repetitive inspections of certain
refuel/defuel tube assemblies in the engine nacelles for fuel leakage,
and corrective action, if necessary. This amendment will also require
eventual modification of all tube assemblies, which will terminate the
repetitive inspections. This amendment is prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by this AD are intended
to prevent fuel leaks and consequent increased risk of engine fires.
[[Page 65010]]
DATES: Effective January 14, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 14, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box
6087, Station A, Montreal, Quebec H3C 3G9, 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, Engine and Propeller Directorate, 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: Richard Fiesel, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, Engine and Propeller Directorate, 10 Fifth
Street, Third Floor, Valley Stream, New York 11581; telephone (516)
256-7504; fax (516) 256-2716.
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 de Havilland Model DHC-8-
100, -200, and -300 series airplanes was published in the Federal
Register on October 6, 1997 (62 FR 52051). That action proposed to
require repetitive inspections of certain refuel/defuel tube assemblies
in the engine nacelles for fuel leakage, and corrective action, if
necessary. It also proposed to require eventual modification of all
tube assemblies, which would terminate the repetitive inspections.
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 95 Model DHC-8-100, -200, and -300 series
airplanes of U.S. registry will be affected by this AD.
The inspection will take approximately 6 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Based on
these figures, the cost impact of the inspection required by this AD on
U.S. operators is estimated to be $34,200, or $360 per airplane, per
inspection cycle.
The modification (specified in Part 2 of the Accomplishment
Instructions in the referenced alert service bulletin) will take
approximately 15 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will cost approximately
$500. Based on these figures, the cost impact of the modification
required by this AD on U.S. operators is estimated to be $133,000, or
$1,400 per airplane.
The modification (specified in Part 3 of the Accomplishment
Instructions in the referenced service bulletin) will take
approximately 36 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will cost approximately
$1,600 per airplane. Based on these figures, the cost impact of the
modification required by this AD on U.S. operators is estimated to be
$357,200, or $3,760 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.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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:
97-25-14 De Havilland, Inc.: Amendment 39-10238. Docket 97-NM-120-
AD.
Applicability: Model DHC-8-100, -200, and -300 series airplanes;
as listed in Bombardier Alert Service Bulletin S.B. A8-28-20,
Revision `A,' dated September 10, 1996; certificated in any
category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 (f) 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 fuel leaks and consequent increased risk of engine
fires, accomplish the following:
(a) Within 30 days after the effective date of this AD, inspect
the five refuel/defuel tube assemblies in the engine nacelles to
detect fuel leaks, in accordance with Part 1 of the Accomplishment
Instructions of Bombardier Alert Service Bulletin S.B. A8-28-20,
Revision `A', dated September 10, 1996. If any fuel leak is found,
prior to further flight, replace the refuel/defuel tube assembly
with an improved assembly, in accordance with the alert service
bulletin. Thereafter, repeat the inspection at intervals not to
exceed 6 months.
(b) Within 12 months after the effective date of this AD, modify
the refuel/defuel tube assembly located under the exhaust fingernail
on the engine nacelle, as specified in Part 2 of the Accomplishment
Instructions of Bombardier Alert Service Bulletin S.B. A8-28-20,
Revision `A,' dated September 10,
[[Page 65011]]
1996, in accordance with the procedures specified in the alert
service bulletin.
(c) Within 24 months after the effective date of this AD, modify
the remaining refuel/defuel tube assemblies, as specified in Part 3
of the Accomplishment Instructions of Bombardier Alert Service
Bulletin S.B. A8-28-20, Revision `A,' dated September 10, 1996, in
accordance with the procedures specified in the alert service
bulletin.
(d) Accomplishment of the modifications required by paragraphs
(b) and (c) of this AD constitutes terminating action for the
repetitive inspections required by paragraph (a) of this AD.
(e) As of the effective date of this AD, no person shall install
a refuel/defuel tube assembly having part number 82820107-007,
82821015-003, 82820108-005, 82820245-001, 82820246-001, 82820247-
001, or 82821014-001, on any airplane.
(f) 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, Engine and Propeller Directorate. 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(g) Special flight permits may be issued in accordance with
Secs. 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.
(h) The actions shall be done in accordance with Bombardier
Alert Service Bulletin S.B. A8-28-20, Revision `A,' dated September
10, 1996. 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.,
Canadair, Aerospace Group, P.O. Box 6087, Station A, Montreal,
Quebec H3C 3G9, Canada. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Engine and Propeller Directorate, 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-96-14, dated August 20, 1996.
(i) This amendment becomes effective on January 14, 1998.
Issued in Renton, Washington, on December 2, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-32118 Filed 12-9-97; 8:45 am]
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