[Federal Register: August 23, 2005 (Volume 70, Number 162)]
[Rules and Regulations]
[Page 49173-49174]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23au05-7]
[[Page 49173]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21341; Directorate Identifier 2003-NM-026-AD;
Amendment 39-14231; AD 2005-17-10]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB 2000 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Saab Model SAAB 2000 airplanes. This AD requires an inspection
for cracking of the fastener holes in the front and rear spars, a
modification of the fastener holes of the front and rear spars and the
rear spar web, and related investigative/corrective actions if
necessary. This AD is prompted by a report of cracking of certain
fastener holes in the lower spar cap of the rear spar and in the lower
skin at the front spar. We are issuing this AD to prevent cracking of
the front and rear spars, which could result in fuel leakage and
consequent reduced structural integrity of the wing structure.
DATES: This AD becomes effective September 27, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of
September 27, 2005.
ADDRESSES: For service information identified in this AD, contact Saab
Aircraft AB, SAAB Aircraft Product Support, S-581.88, Link[ouml]ping,
Sweden.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S.
Department of Transportation, 400 Seventh Street SW, room PL-401,
Washington, DC. This docket number is FAA-2005-21341; the directorate
identifier for this docket is 2003-NM-026-AD.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for certain Saab Model SAAB 2000 airplanes. That action,
published in the Federal Register on June 3, 2005 (70 FR 32540),
proposed to require an inspection for cracking of the fastener holes in
the front and rear spars, a modification of the fastener holes of the
front and rear spars and the rear spar web, and related investigative/
corrective actions if necessary.
New Relevant Service Information
Saab has issued Service Bulletin 2000-57-038, Revision 01, dated
June 24, 2004. The proposed AD refers to Saab Service Bulletin 2000-57-
038, dated December 18, 2002, as the acceptable source of service
information for doing the proposed actions. The procedures in Revision
01 of the service bulletin are essentially the same as those in the
original issue. Therefore, we have revised paragraphs (f) and (g) of
this AD to refer to Revision 01 of the service bulletin as the
appropriate source of service information for doing the actions
required by those paragraphs. We have also added a new paragraph (h) to
this AD (and re-identified subsequent paragraphs accordingly) to give
credit for actions done before the effective date of this AD in
accordance with the original issue of the service bulletin.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been submitted on the proposed
AD or on the determination of the cost to the public.
Explanation of Change to Applicability
The FAA has revised the applicability of this AD to identify model
designations as published in the most recent type certificate data
sheet for the affected models.
Conclusion
We have carefully reviewed the available data, and determined that
air safety and the public interest require adopting the AD with the
changes described previously. We have determined that these changes
will neither increase the economic burden on any operator nor increase
the scope of the AD.
Costs of Compliance
This AD affects about 3 airplanes of U.S. registry. The required
actions (inspections and modification) will take about 250 work hours
per airplane, at an average labor rate of $65 per work hour. Required
parts will cost about $8,557 per airplane. Based on these figures, the
estimated cost of this AD for U.S. operators is $74,421, or $24,807 per
airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
[[Page 49174]]
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-17-10 SAAB Aircraft AB: Amendment 39-14231. Docket No. FAA-
2005-21341; Directorate Identifier 2003-NM-026-AD.
Effective Date
(a) This AD becomes effective September 27, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to certain Saab Model SAAB 2000 airplanes
having serial numbers 004 through 063 inclusive, certificated in any
category.
Unsafe Condition
(d) This AD was prompted by a report of cracking of certain
fastener holes in the lower spar cap of the rear spar and in the
lower skin at the front spar. We are issuing this AD to prevent
cracking of the front and rear spars, which could result in fuel
leakage and consequent reduced structural integrity of the wing
structure.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection
(f) Prior to the accumulation of 20,000 total flight cycles,
perform non-destructive tests for cracking of the fastener holes in
the lower spar cap of the rear spar and in the lower skin at the
left-hand and right-hand sides of the front spar, between WS20 and
WS83 inclusive; by accomplishing all the actions specified in Parts
A, B, and C of the Accomplishment Instructions of Saab Service
Bulletin 2000-57-038, Revision 01, dated June 24, 2004. If any
cracking is detected, before further flight, repair the cracking
according to a method approved by the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA; or the Luftfartsverket
(LFV) (or its delegated agent).
Modification
(g) Prior to the accumulation of 20,000 total flight cycles,
modify the fastener holes of the front and rear spars and the rear
spar web, including related investigative actions, by accomplishing
all the actions specified in Part D of the Accomplishment
Instructions of Saab Service Bulletin 2000-57-038, Revision 01,
dated June 24, 2004. If \1/4\-inch fasteners are needed for holes
No. 7 and No. 8, before further flight, contact the Manager,
International Branch, ANM-116, for further actions, or the LFV (or
its delegated agent). If any scratches or other damage is detected
on the skin surface or the surface of the front spar, before further
flight, repair in accordance with a method approved by the Manager,
International Branch, ANM-116, or the LFV (or its delegated agent).
Actions Accomplished Previously
(h) Inspections or modifications accomplished before the
effective date of this AD in accordance with the Accomplishment
Instructions of Saab Service Bulletin 2000-57-038, dated December
18, 2002, are considered acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance (AMOCs)
(i) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(j) You must use Saab Service Bulletin 2000-57-038, Revision 01,
dated June 24, 2004, to perform the actions that are required by
this AD, unless the AD specifies otherwise. The Director of the
Federal Register approves the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To
get copies of the service information, contact Saab Aircraft AB,
SAAB Aircraft Product Support, S-581.88, Link[ouml]ping, Sweden. To
view the AD docket, go to the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Nassif Building, Washington, DC. To review copies of the service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at the
NARA, call (202) 741-6030, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html
.
Issued in Renton, Washington, on August 11, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-16456 Filed 8-22-05; 8:45 am]
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