[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]


=======================================================================
-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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]
BILLING CODE 4910-13-U