[Federal Register Volume 64, Number 218 (Friday, November 12, 1999)]
[Rules and Regulations]
[Pages 61478-61480]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-28746]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-335-AD; Amendment 39-11401; AD 99-23-05]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-101, -102, -103,
-106, -201, -202, -301, -311, and -315 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Bombardier Model DHC-8-101, -102, -103, -106, -201, -
202, -301, -311, and -315 series airplanes, that requires repetitive
detailed visual inspections and high frequency eddy current inspections
to detect cracking of the wing upper skin and ladder plates at over
wing access panels between certain stations; and repair, if necessary.
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 detect and correct
fatigue cracking of the wing ladder plates, which, if not corrected,
could reduce the structural integrity of the wing.
DATES: Effective December 17, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 17, 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,
[[Page 61479]]
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: Franco Pieri, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 10 Fifth Street,
Third Floor, Valley Stream, New York 11581; telephone (516) 256-7526;
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 all Bombardier Model DHC-8-101, -
102, -103, -106, -201, -202, -301, -311, and -315 series airplanes was
published in the Federal Register on September 3, 1999 (64 FR 48333).
That action proposed to require repetitive detailed visual inspections
and high frequency eddy current inspections to detect cracking of the
wing upper skin and ladder plates at over wing access panels between
certain stations; and repair, if necessary.
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 166 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 40 work hours per
airplane to accomplish the inspections, and that the average labor rate
is $60 per work hour. Based on these figures, the cost impact of this
AD on U.S. operators is estimated to be $398,400, or $2,400 per
airplane, per inspection cycle.
The cost impact figure discussed above is 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:
99-23-05 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-11401. Docket 98-NM-335-AD.
Applicability: All Model DHC-8-101, -102, -103, -106, -201, -
202, -301, -311, and -315 series airplanes, 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 detect and correct fatigue cracking of the wing ladder
plates, which if not corrected, could reduce the structural
integrity of the wing, accomplish the following:
Inspection for DHC-8-100 and -300 Series Airplanes
(a) At the applicable compliance time listed in paragraph
(a)(1), (a)(2), or (a)(3) of this AD, perform a detailed visual
inspection to detect cracking of the skin and a high frequency eddy
current (HFEC) inspection of the ladder plates at over wing access
panels between station YW42.00 and YW171.20, in accordance with de
Havilland Temporary Revision MTC-15, dated September 18, 1998, of
the de Havilland Maintenance Program Manual PSM 1-8-7 TC (for Model
DHC-8-100 series airplanes); or de Havilland Temporary Revision MTC
3-14, dated September 18, 1998, of the de Havilland Maintenance
Program Manual PSM 1-83-7TC (for Model DHC-8-300 series airplanes);
as applicable. Repeat the inspections thereafter at intervals not to
exceed 10,000 flight cycles.
(1) For airplanes that have accumulated 5,000 or fewer total
flight cycles as of the effective date of this AD, accomplish the
inspection prior to the accumulation of 10,000 total flight cycles.
(2) For airplanes that have accumulated more than 5,000 total
flight cycles, but fewer than 38,501 total flight cycles as of the
effective date of this AD, accomplish the inspection prior to the
accumulation of [5,522+(0.8955 x N Accumulated)] total cycles. ``N
Accumulated'' is defined as the total number of flight cycles as of
the effective date of this AD.
(3) For airplanes that have accumulated 38,501 or more total
flight cycles as of the effective date of this AD, accomplish the
inspection within 1,500 flight cycles after the effective date of
this AD.
Note 2: 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.''
Inspection for DHC-8-200 Series Airplanes
(b) At the applicable compliance time listed in paragraph (b)(1)
or (b)(2) of this AD, perform a detailed visual inspection of the
skin and an HFEC inspection to detect cracking of the ladder plates
at over wing access panels between station YW42.00 and YW171.20, in
accordance with de Havilland Temporary Revision MTC 2-14, dated
September 18, 1998, of the de Havilland Maintenance Program Manual
PSM 1-82-7TC. Repeat the inspections thereafter at intervals not to
exceed 10,000 flight cycles.
[[Page 61480]]
(1) For airplanes that have accumulated 5,000 or fewer total
flight cycles as of the effective date of this AD, accomplish the
inspection prior to the accumulation of 10,000 total flight cycles.
(2) For airplanes that have accumulated more than 5,000 total
flight cycles, but fewer than 38,501 total flight cycles as of the
effective date of this AD, accomplish the inspection prior to the
accumulation of [5,522+(0.8955 x N Accumulated)] total cycles,
where ``N Accumulated'' is defined as the total number of flight
cycles as of the effective date of this AD.
Repair
(c) If any crack is detected during any inspection required by
this AD, prior to further flight, repair in accordance with a method
approved by the Manager, New York Aircraft Certification Office
(ACO), FAA, Engine and Propeller Directorate; or the Transport
Canada Civil Aviation (TCCA) (or its delegated agent). For a repair
method to be approved by the Manager, New York ACO, as required by
this paragraph, the Manager's approval letter must specifically
reference 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, 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 3: 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
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) Except as provided by paragraph (c) of this AD, the actions
shall be done in accordance with de Havilland Temporary Revision
MTC-15, dated September 18, 1998, of the de Havilland Maintenance
Program Manual PSM 1-8-7 TC; de Havilland Temporary Revision MTC 3-
14, dated September 18, 1998, of the de Havilland Maintenance
Program Manual PSM 1-83-7 TC; or de Havilland Temporary Revision MTC
2-14, dated September 18, 1998, of the de Havilland Maintenance
Program Manual PSM 1-82-7 TC; 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 4: The subject of this AD is addressed in Canadian
airworthiness directive CF-98-30, dated August 31, 1998.
(g) This amendment becomes effective on December 17, 1999.
Issued in Renton, Washington, on October 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-28746 Filed 11-10-99; 8:45 am]
BILLING CODE 4910-13-P
