[Federal Register Volume 61, Number 227 (Friday, November 22, 1996)]
[Rules and Regulations]
[Pages 59315-59317]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-28869]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-NM-194-AD; Amendment 39-9814; AD 96-23-09]
RIN 2120-AA64
Airworthiness Directives; de Havilland Model DHC-8-100 and -300
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain de Havilland Model DHC-8-100 and -300
series airplanes, that currently requires repetitive inspections to
detect cracks of the upper drag strut trunnion fittings of the nose
landing gear (NLG) and to verify tightness of the fitting attachment
bolts, and replacement of fittings or fasteners, if necessary. This
amendment requires the installation of a modification to terminate the
repetitive inspections. This amendment is prompted by the development
of a modification that positively addresses the identified unsafe
condition. The actions specified by this AD are intended to prevent
failure of the upper drag strut trunnion fittings of the NLG, which
could lead to collapse of the NLG.
DATES: Effective December 27, 1996.
The incorporation by reference of de Havilland DHC-8 Alert Service
Bulletin S.B. A8-53-40, Revision `D', dated June 30, 1995; and de
Havilland DHC-8 Service Bulletin S.B. 8-53-49, dated June 30, 1995, as
listed in the regulations, is approved by the Director of the Federal
Register as of December 27, 1996.
The incorporation by reference of certain other publications, as
listed in the regulations was approved previously by the Director of
the Federal Register
[[Page 59316]]
as of May 27, 1993 (58 FR 25549, April 27, 1993).
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, New York Aircraft Certification Office,
Engine and Propeller Directorate, 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: Jon Hjelm, Aerospace Engineer,
Airframe Branch, ANE-172, FAA, Engine and Propeller Directorate, New
York Aircraft Certification Office, 181 South Franklin Avenue, Room
202, Valley Stream, New York 11581; telephone (516) 256-7523; fax (516)
568-2716.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 93-08-03,
amendment 39-8550 (58 FR 25549, April 27, 1993), which is applicable to
certain de Havilland Model DHC-8-100 and -300 series airplanes, was
published as a supplemental notice of proposed rulemaking (NPRM) in the
Federal Register on September 9, 1996 (61 FR 47459). The action
proposed to supersede AD 93-08-03 to continue to require repetitive
inspections to detect cracks of the upper drag strut trunnion fittings
of the nose landing gear (NLG) and to verify tightness of the fitting
attachment bolts, and replacement of the fittings or fasteners, if
necessary. That action also proposed to require the installation of a
modification to terminate the repetitive inspections. Additionally, the
action also proposed revise the applicability of the existing AD.
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 146 de Havilland Model DHC-8-100 and -300
series airplanes of U.S. registry will be affected by this AD.
Accomplishment of the currently required inspections takes
approximately 1 work hour per airplane, at an average labor rate of $60
per hour. Based on these figures, the cost impact of the currently
required inspection actions on U.S. operators is estimated to be
$8,760, or $60 per airplane, per inspection.
The modification will take approximately 18 work hours per airplane
to accomplish, at an average labor rate of $60 per work hour. Required
parts will cost approximately $3,325 per airplane. Based on these
figures, the cost impact of the AD on U.S. operators is estimated to be
$638,725, or $4,405 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 removing amendment 39-8550 (58 FR
25549, April 27, 1993), and by adding a new airworthiness directive
(AD), amendment 39-9814, to read as follows:
96-23-09 De Havilland, Inc.: Amendment 39-9814. Docket 93-NM-194-
AD. Supersedes AD 93-08-03, Amendment 39-8550.
Applicability: Model DHC-8-102, -103, -301, -311, and -314
series airplanes; having serial numbers 003 through 395 inclusive,
but excluding serial numbers 011, 362, and 391; on which
Modification 8/2139 (as described in de Havilland Service Bulletin
S.B. 8-53-49, dated June 30, 1995) has not been accomplished;
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 (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 failure of the upper drag strut trunnion fittings of
the nose landing gear (NLG), which could lead to collapse of the
NLG, accomplish the following:
(a) Within 500 landings after May 27, 1993 (the effective date
of AD 93-08-03, Amendment 39-8550), unless accomplished within the
last 500 landings, conduct a visual inspection of both upper drag
strut trunnion fittings of the NLG to detect cracks; and conduct an
inspection of the fitting attachment bolts to verify tightness; in
accordance with de Havilland DHC-8 Alert Service Bulletin S.B. A8-
53-40, Revision `A', dated June 12, 1992; or Revision `B', dated
February 24, 1993; or Revision `D', dated June 30, 1995.
(1) If no crack is detected in the upper drag strut trunnion
fittings of the NLG, and no looseness is detected in the fitting
attachment bolts, repeat the inspections at intervals not to exceed
1,000 landings until the modification required by paragraph (b) of
this AD is accomplished.
(2) If any crack is detected on either fitting, prior to further
flight, replace both fittings
[[Page 59317]]
with confirmed crack-free fittings in accordance with the service
bulletin. After such replacement, the inspections required by this
paragraph must continue at intervals not to exceed 1,000 landings
until the modification required by paragraph (b) of this AD is
accomplished.
(3) If any fitting attachment bolt is found to be loose during
the initial inspection, prior to further flight, replace the
fasteners (nut, washer, and bolt) that secure the fitting, in
accordance with the service bulletin. After such replacement, the
inspections required by this paragraph must continue at intervals
not to exceed 1,000 landings until the modification required by
paragraph (b) of this AD is accomplished.
(4) If any fastener is found to be loose during any repetitive
inspection required by this AD, prior to further flight, tighten the
bolt to the value specified in the service bulletin.
(b) Within 6 months after the effective date of this AD, install
Modification 8/2139 in accordance with de Havilland Service Bulletin
S.B. 8-53-49, dated June 30, 1995. Installation of this modification
constitutes terminating action for the inspection requirements of
this AD.
(c) Installation of Modification 8/2139, in accordance with de
Havilland Service Bulletin S.B. 8-53-49, dated June 30, 1995,
constitutes terminating action for the inspections required by this
AD.
(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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(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.
(f) The actions shall be done in accordance with de Havilland
DHC-8 Alert Service Bulletin S.B. A8-53-40, Revision `A', dated June
12, 1992 Revision `B', dated February 24, 1993, Revision `D', dated
June 30, 1995; and de Havilland Service Bulletin S.B. 8-53-49, dated
June 30, 1995. The incorporation by reference of de Havilland DHC-8
Alert Service Bulletin S.B. A8-53-40, Revison `A', dated June 12,
1992; and Revision `B', dated February 24, 1993, was approved
previously by the Director of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51 as of May 27, 1993 (58 FR
25549, April 27, 1993). The incorporation by reference of de
Havilland DHC-8 Alert Service Bulletin S.B. A8-53-40, Revision `D',
dated June 30, 1995; and de Havilland Service Bulletin S.B. 8-53-49,
dated June 30, 1995, is 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, New York Aircraft Certification Office, Engine and Propeller
Directorate, 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.
(g) This amendment becomes effective on December 27, 1996.
Issued in Renton, Washington, on November 5, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-28869 Filed 11-21-96; 8:45 am]
BILLING CODE 4910-13-U
