[Federal Register Volume 66, Number 78 (Monday, April 23, 2001)]
[Rules and Regulations]
[Pages 20377-20378]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-9666]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 66, No. 78 / Monday, April 23, 2001 / Rules
and Regulations
[[Page 20377]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NM-181-AD; Amendment 39-12182; AD 2001-08-05]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-7-100, -101, -102,
and -103 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-7-100, -101, -102, and -103
series airplanes, that requires inspecting the endcaps of the main
landing gear selector valve for leaks of hydraulic oil and, if leaks
are detected, replacing the leaking endcaps or the entire selector
valve. This amendment also requires eventual replacement or rework of
certain selector valves, which would terminate the repetitive
inspections. This amendment is prompted by a report of the collapse of
the main landing gear due to an external leak of hydraulic oil in the
landing gear selector valve, resulting from a fracture of the endcap.
The actions specified by this AD are intended to prevent leaks of
hydraulic oil from the main landing gear selector valve, which could
result in the collapse of the main landing gear.
DATES: Effective May 29, 2001.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 29, 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 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.
FOR FURTHER INFORMATION CONTACT: James E. Delisio, Aerospace Engineer,
ANE-171, FAA, New York Aircraft Certification Office, 10 Fifth Street,
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7521;
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-7-
100, -101, -102, and -103 series airplanes was published in the Federal
Register on October 12, 2000 (65 FR 60595). That action proposed to
require inspecting the endcaps of the main landing gear selector valve
for leaks of hydraulic oil and, if leaks are detected, replacing the
leaking endcaps or the entire selector valve. That action also proposed
to require eventual replacement or rework of certain selector valves,
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.
Explanation of Change to Final Rule
Since the issuance of the proposed rule, the FAA has received
information from an operator indicating that replacement of the
existing aluminum endcaps with stainless steel endcaps having part
number (P/N) 52982, on a main landing gear selector valve having P/N
57420-5, is the same terminating action as that specified in paragraph
(c)(2) of the final rule. The FAA has determined that this is accurate
information and has changed the final rule to specify that such
replacement constitutes terminating action for the repetitive
inspections required by paragraph (a) of the final rule. Paragraphs
(b)(1) and (c)(2) of the final rule have been revised for
clarification.
Conclusion
After careful review of the available data, the FAA has determined
that air safety and the public interest require the adoption of the
rule with the changes described previously. The FAA has determined that
these changes will neither increase the economic burden on any operator
nor increase the scope of the AD.
Cost Impact
The FAA estimates that 32 airplanes of U.S. registry will be
affected by this AD, that it will require 1 work hour per airplane to
accomplish the inspection, and that the average labor rate is $60 per
work hour. Based on these figures, the cost impact of the inspection on
U.S. operators is estimated to be $1,920, or $60 per airplane.
The FAA also estimates that it will require 5 work hours per
airplane to rework or replace the main landing gear selector valve and
that the average labor rate is $60 per work hour. Based on these
figures, the cost impact of the rework or replacement on U.S. operators
is estimated to be $9,600 or $300 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.
Should an operator elect to replace the endcaps and perform the
optional repetitive inspections prior to replacing the main landing
gear selector valve, it would take approximately 1 work hour per
airplane to conduct each inspection. Based on these figures, the cost
impact of the optional repetitive inspections is estimated to be $60
per inspection per airplane.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect on
[[Page 20378]]
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:
2001-08-05 Bombardier, Inc. (Formerly de Havilland, Inc.):
Amendment 39-12182. Docket 2000-NM-181-AD.
Applicability: Model DHC-7-100, -101, -102, and -103 series
airplanes, serial numbers 003 through 113 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 the collapse of the main landing gear due to leaks of
hydraulic oil from the main landing gear selector valve, accomplish
the following:
Inspection
(a) Within 100 flight cycles after the effective date of this
AD, perform a general visual inspection of both endcaps of the main
landing gear selector valve for the presence of hydraulic oil, in
accordance with the Accomplishment Instructions of Bombardier Alert
Service Bulletin A7-32-103, dated September 3, 1999. If no hydraulic
oil is detected on either endcap, repeat the inspection at intervals
not to exceed 400 flight hours until the requirements of paragraph
(c) of this AD are accomplished.
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.''
Replacement or Modification
(b) If any hydraulic oil is detected on either endcap: Prior to
further flight, perform the actions specified in either paragraph
(b)(1) or (b)(2) of this AD.
(1) Replace the existing aluminum endcaps (on the selector
valve), part number (P/N) 34629, with new stainless steel endcaps
having P/N 52982, in accordance with the Accomplishment Instructions
of Bombardier Alert Service Bulletin A7-32-103, dated September 3,
1999. For main landing gear selector valves having P/N 57420-5,
replacement of the endcaps terminates the repetitive inspection
requirements of this AD.
(2) Replace the main landing gear selector valve with a valve
having P/N 57420-5A, in accordance with the Accomplishment
Instructions of Bombardier Alert Service Bulletin A7-32-103, dated
September 3, 1999.
Note 3: Use care when removing the endcaps, so that the internal
components do not fall on the ground and get damaged.
(c) Within 12 months after the effective date of this AD:
Perform the actions specified in either paragraph (c)(1) or (c)(2)
of this AD, in accordance with the Accomplishment Instructions of
Bombardier Alert Service Bulletin A7-32-103, dated September 3,
1999. Accomplishment of either paragraph (c)(1) or (c)(2) terminates
the repetitive inspection requirements of this AD.
(1) If a main landing gear selector valve having P/N 57420-1 or
57420-3 is installed, remove it and replace it with a valve having
P/N 57420-5A.
(2) If a main landing gear selector valve having P/N 57420-5 is
installed, remove it and replace it with a valve having P/N 57420-5A
or modify the valve to the P/N 57420-5A configuration (Modification
7/2742). For main landing gear selector valves having P/N 57420-5,
replacement of the endcaps, as specified in paragraph (b)(1) of this
AD, terminates the repetitive inspection requirements of 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 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
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.
Incorporation by Reference
(f) The actions shall be done in accordance with Bombardier
Alert Service Bulletin A7-32-103, dated September 3, 1999. 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-99-31, dated December 21, 1999.
Effective Date
(g) This amendment becomes effective on May 29, 2001.
Issued in Renton, Washington, on April 12, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 01-9666 Filed 4-20-01; 8:45 am]
BILLING CODE 4910-13-U