[Federal Register Volume 64, Number 178 (Wednesday, September 15, 1999)]
[Rules and Regulations]
[Pages 49964-49966]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-23352]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-220-AD; Amendment 39-11310; AD 99-19-21]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B
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 Saab Model SAAB SF340A and SAAB 340B series
airplanes, that requires repetitive inspections to detect cracking
around certain fastener holes and adjacent areas of the front spar of
the horizontal stabilizers; and corrective actions, if necessary. This
amendment also requires repetitive x-ray inspections, cold working of
certain fastener holes of the front spar of the horizontal stabilizers,
and follow-on actions; and installation of new fasteners, which
constitutes terminating action for the repetitive inspections required
by this AD. This amendment is prompted by the issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The actions specified by this AD are intended to prevent
failure of the front spar due to fatigue cracking around certain
fastener holes of the front spar of the horizontal stabilizers, which
could result in reduced structural integrity of the airplane.
DATES: Effective October 20, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 20, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Saab Aircraft AB, SAAB Aircraft Product Support, S-
581.88, Linkoping, Sweden. 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
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
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 Saab Model SAAB SF340A and
SAAB 340B series airplanes was published as a supplemental notice of
proposed rulemaking (NPRM) in the Federal Register on July 15, 1999 (64
FR 38150). That action proposed to require repetitive inspections to
detect cracking around certain fastener holes and adjacent areas of the
front spar of the horizontal stabilizers; and corrective actions, if
necessary. That action also proposed to require cold working of certain
fastener holes of the front spar of the horizontal stabilizers, and
follow-on actions; and installation of new fasteners, which would
constitute terminating action for the repetitive inspections. That
action also proposed to add repetitive x-ray 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 Made to Final Rule
The FAA has added a note to the final rule to clarify the
definition of a detailed visual inspection.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change described
previously. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 279 airplanes of U.S. registry will be
affected by this AD.
[[Page 49965]]
It will take approximately 4 work hours per airplane to perform the
required detailed visual inspection, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of the
inspection required by this AD on U.S. operators is estimated to be
$66,960, or $240 per airplane, per inspection cycle.
It will take approximately 6 work hours per airplane to accomplish
the required eddy current and x-ray inspections, at an average labor
rate of $60 per work hour. Based on these figures, the cost impact of
the inspections required by this AD on U.S. operators is estimated to
be $100,440, or $360 per airplane, per inspection cycle.
It will take approximately 42 work hours to accomplish the cold
working of the fastener holes, at an average labor rate of $60 per work
hour. Required parts will cost approximately $400 per airplane. Based
on these figures, the cost impact of the cold work required by this AD
on U.S. operators is estimated to be $814,680, or $2,920 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 adding the following new
airworthiness directive:
99-19-21 SAAB Aircraft AB: Amendment 39-11310. Docket 98-NM-220-
AD.
Applicability: Model SAAB SF340A series airplanes,
manufacturer's serial numbers -004 through -159 inclusive; and SAAB
340B series airplanes, manufacturer's serial numbers -160 through -
439 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 (f) 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 front spar due to fatigue cracking
around certain fastener holes of the front spar of the horizontal
stabilizers, which could result in reduced structural integrity of
the airplane, accomplish the following:
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.''
Initial and Repetitive Inspections
(a) For Model SAAB SF340A series airplanes with manufacturer's
serial numbers -004 through -159 inclusive: Perform the inspections
(detailed visual, eddy current, and x-ray) specified in paragraph
2.D. of the Accomplishment Instructions of Saab Service Bulletin
340-55-033, Revision 04, dated December 1, 1998, to detect cracking
around certain fastener holes and adjacent areas of the front spar
of the horizontal stabilizer, in accordance with the service
bulletin, at the time specified in paragraph (a)(1), (a)(2), or
(a)(3) of this AD, as applicable. Thereafter, repeat only the eddy
current and x-ray inspections at intervals not to exceed 12,000
flight cycles until the requirements of paragraph (d) of this AD are
accomplished.
(1) For airplanes that have accumulated less than 22,000 total
flight cycles as of the effective date of this AD: Perform an eddy
current and an x-ray inspection prior to the accumulation of 22,000
total flight cycles, or within 2,000 flight cycles after the
effective date of this AD, whichever occurs later.
(2) For airplanes that have accumulated 22,000 or more total
flight cycles and less than 30,000 total flight cycles as of the
effective date of this AD: Accomplish the requirements of paragraphs
(a)(2)(i) and (a)(2)(ii) of this AD.
(i) Perform a detailed visual inspection within 800 flight
cycles after the effective date of this AD; and
(ii) Perform an eddy current and an x-ray inspection within
2,000 flight cycles after the effective date of this AD.
(3) For airplanes that have accumulated 30,000 or more total
flight cycles as of the effective date of this AD: Accomplish the
requirements of paragraphs (a)(3)(i) and (a)(3)(ii) of this AD.
(i) Perform a detailed visual inspection within 400 flight
cycles after the effective date of this AD; and
(ii) Perform an eddy current and an x-ray inspection within
1,200 flight cycles after the effective date of this AD.
Initial and Repetitive Inspections
(b) For Model SAAB 340B series airplanes with manufacturer's
serial numbers -160 through -439 inclusive: Perform the inspections
(detailed visual, eddy current, and x-ray) specified in paragraph
2.D. of the Accomplishment Instructions of Saab Service Bulletin
340-55-033, Revision 04, dated December 1, 1998, to detect cracking
around certain fastener holes and adjacent areas of the front spar
of the horizontal stabilizer, in accordance with the service
bulletin, at the time specified in paragraph (b)(1), (b)(2), or
(b)(3) of this AD, as applicable. Thereafter, repeat only the eddy
current and x-ray inspections at intervals not to exceed 6,000
flight cycles until the requirements of paragraph (d) of this AD are
accomplished.
(1) For airplanes that have accumulated less than 12,000 total
flight cycles as of the effective date of this AD: Perform an eddy
current and an x-ray inspection prior to the accumulation of 12,000
total flight cycles, or within 2,000 flight cycles after the
effective date of this AD, whichever occurs later.
(2) For airplanes that have accumulated 12,000 or more total
flight cycles and less than 16,000 total flight cycles as of the
effective date of this AD: Accomplish the requirements of paragraphs
(b)(2)(i) and (b)(2)(ii) of this AD.
[[Page 49966]]
(i) Perform a detailed visual inspection within 800 flight
cycles after the effective date of this AD; and
(ii) Perform an eddy current and an x-ray inspection within
2,000 flight cycles after the effective date of this AD.
(3) For airplanes that have accumulated 16,000 or more total
flight cycles as of the effective date of this AD: Accomplish the
requirements of paragraphs (b)(3)(i) and (b)(3)(ii) of this AD.
(i) Perform a detailed visual inspection within 400 flight
cycles after the effective date of this AD; and
(i) Perform a detailed visual inspection within 400 flight
cycles after the effective date of this AD; and (ii) Perform an eddy
current and an x-ray inspection within 1,200 flight cycles after the
effective date of this AD.
Corrective Actions
(c) If any cracking is detected during any inspection required
by paragraph (a) or (b) of this AD, prior to further flight, either
repair in accordance with a method approved by the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
or the Luftfartsverket (LFV) (or its delegated agent); or accomplish
the requirements of paragraph (d) of this AD.
Note 3: Inspections to detect cracking around certain fastener
holes and adjacent areas of the front spar of the horizontal
stabilizers that have been accomplished prior to the effective date
of this AD in accordance with Saab Service Bulletin 340-55-033,
Revision 03, dated January 22, 1998, are considered acceptable for
compliance with the applicable action specified by this AD.
Terminating Action
(d) For all airplanes: Except as provided by paragraph (e) of
this AD, accomplish cold working of certain fastener holes of the
front spar of the horizontal stabilizers, and follow-on actions; and
install new fasteners; in accordance with Saab Service Bulletin 340-
55-034, dated October 16, 1998; at the time specified in paragraph
(d)(1), (d)(2), or (d)(3) of this AD, as applicable. Accomplishment
of this action constitutes terminating action for this AD.
(1) For all airplanes that have accumulated less than 26,000
total flight cycles as of the effective date of this AD: Within
10,000 flight cycles after the effective date of this AD.
(2) For all airplanes that have accumulated 26,000 or more total
flight cycles and less than 30,000 total flight cycles as of the
effective date of this AD: Within 6,000 flight cycles after the
effective date of this AD.
(3) For all airplanes that have accumulated 30,000 or more total
flight cycles as of the effective date of this AD: Within 3,000
flight cycles after the effective date of this AD.
(e) If any crack is detected during the accomplishment of
paragraph (d) of this AD, and if the service bulletin listed in
paragraph (d) of this AD specifies to contact the manufacturer for
an appropriate corrective action: Prior to further flight, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, or the LFV (or its delegated agent).
Alternative Method of Compliance
(f) 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, International Branch, ANM-116.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, International Branch, ANM-116.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(g) 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
(h) Except as provided by paragraphs (c) and (e) of this AD, the
actions shall be done in accordance with Saab Service Bulletin 340-
55-033, Revision 04, dated December 1, 1998; and Saab Service
Bulletin 340-55-034, dated October 16, 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 Saab Aircraft AB, SAAB Aircraft
Product Support, S-581.88, Linkoping, Sweden. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; 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 Swedish
airworthiness directives 1-110R2, dated December 7, 1998, and 1-133,
dated October 20, 1998.
(i) This amendment becomes effective on October 20, 1999.
Issued in Renton, Washington, on September 1, 1999.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-23352 Filed 9-14-99; 8:45 am]
BILLING CODE 4910-13-P
