[Federal Register Volume 64, Number 183 (Wednesday, September 22, 1999)]
[Rules and Regulations]
[Pages 51199-51200]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-24148]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-58-AD; Amendment 39-11321; AD 99-19-34]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-100 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 and -300 series
airplanes, that requires modification of certain hydraulic systems that
provide hydraulic pressure for the control of the rudder and for the
main landing gear brakes. 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 damage to certain hydraulic system components in the number
2 engine nacelle, which could result in loss of the number 1 and number
2 hydraulic systems, and consequent reduced controllability of the
airplane.
DATES: Effective October 27, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 27, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division,
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, 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:
Anthony Gallo, Aerospace Engineer, Systems and Flight Test Branch, ANE-
172, FAA, Engine and Propeller Directorate, New York Aircraft
Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New
York 11581; telephone (516) 256-7510; 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
and -300 series airplanes was published in the Federal Register on July
7, 1999 (64 FR 36624). That action proposed to require modification of
certain hydraulic systems that provide hydraulic pressure for the
control of the rudder and for the main landing gear brakes.
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 148 airplanes of U.S. registry will be
affected by this AD.
For airplanes identified in Bombardier Service Bulletin S.B. 8-32-
128, Revision `C,' it will take between 15 and 40 works hours per
airplane to accomplish the required modification, at an average labor
rate of $60 per work hour. Required parts will be provided by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the modification required by this AD on U.S. operators
is estimated to be between $133,200 and $355,200, or between $900 and
$2,400 per airplane.
For airplanes identified in Bombardier Service Bulletin S.B. 8-29-
23, it will take approximately 346 work hours per airplane to
accomplish the required relocation, at an average labor rate of $60 per
work hour. Required parts will be provided by the manufacturer at no
cost to the operators. Based on these figures, the cost impact of the
modification required by this AD on U.S. operators is estimated to be
$3,072,480, or $20,760 per airplane.
For airplanes identified in Bombardier Service Bulletin S.B. 8-29-
29, it will take approximately 120 work hours per airplane to
accomplish the required installation, at an average labor rate of $60
per work hour. Required parts will be provided by the manufacturer at
no cost to the operators. Based on these figures, the cost impact of
the installation required by this AD on U.S. operators is estimated to
be $1,065,600, or $7,200 per airplane.
[[Page 51200]]
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:
99-19-34 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-11321. Docket 97-NM-58-AD.
Applicability: Model DHC-8-100 and -300 series airplanes having
serial numbers 003 through 405; except those airplanes on which
Bombardier Modifications 8/1152 and 8/1982 have been installed, and
on which either Bombardier Modification 8/1983 or 8/2781 has been
installed; 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 (c) 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 damage to certain hydraulic system components in the
number 2 engine nacelle, which could result in loss of the number 1
and number 2 hydraulic systems, and consequent reduced
controllability of the airplane, accomplish the following:
(a) Within 18 months after the effective date of this AD, modify
certain hydraulic systems that provide hydraulic pressure for the
control of the rudder and for the main landing gear brakes by
accomplishing the requirements of paragraph (a)(1) or (a)(2), as
applicable, in accordance with Bombardier Service Bulletin S.B. 8-
32-128, Revision `C,' dated March 27, 1998.
(1) For all airplanes on which Bombardier Modification 8/1152
has been installed: Accomplish Part A of the Accomplishment
Instructions of the service bulletin.
(2) For all airplanes on which Bombardier Modification 8/1152
has not been installed: Accomplish Part B of the Accomplishment
Instructions of the service bulletin.
(b) Within 18 months after the effective date of this AD,
accomplish the actions specific in either paragraph (b)(1) or (b)(2)
of this AD.
(1) Relocate the number 2 standby power unit (SPU) of the number
2 hydraulic system in accordance with Bombardier Service Bulletin
S.B. 8-29-23, dated December 6, 1996; or
(2) Install a hydraulic rudder isolation system in the number 1
and number 2 hydraulic systems in accordance with Bombardier Service
Bulletin S.B. 8-29-29, dated February 27, 1998.
(c) 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.
(d) 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
(e) The actions shall be done in accordance with Bombardier
Service Bulletin S.B. 8-32-128, Revision `C,' dated March 27, 1998;
Bombardier Service Bulletin S.B. 8-29-23, dated December 6, 1996; or
Bombardier Service Bulletin S.B. 8-29-29, dated February 27, 1998;
as applicable. 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, 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, 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 directives CF-96-25R1, dated January 16, 1997, and CF-
96-25R2, dated September 10, 1998.
(f) This amendment becomes effective on October 27, 1999.
Issued in Renton, Washington, on September 10, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-24148 Filed 9-21-99; 8:45 am]
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