[Federal Register Volume 62, Number 238 (Thursday, December 11, 1997)]
[Proposed Rules]
[Pages 65231-65233]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-32424]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-145-AD]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB 2000 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Saab Model SAAB 2000
series airplanes. This proposal would require repetitive visual
inspections to detect discrepancies of the bushing installation
[[Page 65232]]
of the aileron actuation fitting, and eventual installation of staked
bushings in the fitting. Accomplishment of such installation terminates
the repetitive inspections. This proposal also provides for an optional
temporary preventive action, which, if accomplished, would allow the
repetitive inspection intervals to be extended until the terminating
action is accomplished. This proposal is prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by the proposed AD are
intended to prevent failure of the fitting lugs due to vibration caused
by loose bushings in the fittings, and consequent reduced
controllability of the airplane.
DATES: Comments must be received by January 12, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-145-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from SAAB Aircraft AB, SAAB Aircraft Product Support, S-
581.88, Linkoping, Sweden. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-145-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 97-NM-145-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Luftfartsverket (LFV), which is the airworthiness authority for
Sweden, notified the FAA that an unsafe condition may exist on certain
Saab Model SAAB 2000 series airplanes. The LFV advises that, during
vibration damping tests, it has been discovered that the bushings in
the aileron actuation fittings can become loose and cause vibration.
Such vibration, if not corrected, could lead to failure of the fitting
lugs, and consequent reduced controllability of the airplane.
Explanation of Relevant Service Information
Saab has issued Service Bulletin SAAB 2000-57-014, Revision 02,
dated February 11, 1997, which describes procedures for repetitive
visual inspections to detect discrepancies of the bushing
installations. In addition, the service bulletin describes procedures
for eventual installation of new staked bushings in the aileron
actuation fitting, which, when accomplished, eliminates the need for
the repetitive inspections. The service bulletin also describes
procedures for an optional temporary preventive action, which entails
various corrective actions and installation of washers on the bushings
of the aileron actuation fittings. Accomplishment of the actions
specified in the service bulletin is intended to adequately address the
identified unsafe condition.
The LFV classified this service bulletin as mandatory and issued
Swedish airworthiness directive (SAD) No. 1-102R1, dated November 8,
1996, in order to assure the continued airworthiness of these airplanes
in Sweden.
FAA's Conclusions
This airplane model is manufactured in Sweden and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the LFV has kept the FAA informed of
the situation described above. The FAA has examined the findings of the
LFV, reviewed all available information, and determined that AD action
is necessary for products of this type design that are certificated for
operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the service bulletin described previously,
except as discussed below.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletin specifies
that the manufacturer may be contacted for disposition of a certain
repair condition, this proposal would require the repair of that
condition to be accomplished in accordance with a method approved by
the FAA.
Cost Impact
The FAA estimates that 1 airplane of U.S. registry would be
affected by this proposed AD.
The FAA estimates that it would take approximately 1 work hour to
accomplish the proposed inspection, and that the average labor rate is
$60 per work hour. Based on these figures, the cost impact of the
proposed inspection on the single U.S. operator is estimated to be $60
per airplane, per inspection cycle.
The FAA estimates that it would take approximately 4 work hours to
accomplish the proposed installation, and that the average labor rate
is $60 per work hour. Required parts would be provided by the
manufacturer at no cost to the operator. Based on these figures, the
cost impact of the proposed installation on the single U.S. operator is
estimated to be $240 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of
[[Page 65233]]
the proposed requirements of this AD action, and that no operator would
accomplish those actions in the future if this AD were not adopted.
Should an operator elect to accomplish the optional temporary
preventive action that would be provided by this AD action, it would
take approximately 1 work hour to accomplish it, at an average labor
rate of $60 per work hour. Required parts would be provided by the
manufacturer at no cost to the operator. Based on these figures, the
cost impact of the optional temporary preventive action would be $60
per airplane.
Regulatory Impact
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
SAAB Aircraft AB: Docket 97-NM-145-AD.
Applicability: Model SAAB 2000 series airplanes having serial
numbers -002 through -023 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
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 (e) 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 fitting lugs, due to vibration caused
by loose bushings in the aileron actuation fittings, which could
result in reduced controllability of the airplane; accomplish the
following:
(a) Within 100 flight hours after the effective date of this AD,
inspect the bushing installations of the left-hand and right-hand
aileron actuation fittings to detect any discrepancies, in
accordance with Saab Service Bulletin 2000-57-014, Revision 02,
dated February 11, 1997.
(1) If no discrepancy is found, repeat the inspection thereafter
at intervals not to exceed 300 flight hours until the requirements
of paragraph (b) of this AD have been accomplished. Accomplishment
of the temporary preventive action specified in paragraph 2.E. of
the Accomplishment Instructions of the service bulletin allows the
repetitive inspections to be accomplished at intervals of 600 flight
hours until the requirements of paragraph (b) of this AD have been
accomplished.
(2) If any discrepancy is found, prior to further flight,
accomplish the requirements of either paragraph (a)(2)(i) or
(a)(2)(ii) of this AD in accordance with the service bulletin.
(i) Except as specified in paragraph (c), accomplish the
installation required by paragraph (b) of this AD. Accomplishment of
this installation constitutes terminating action for the
requirements of this AD. Or
(ii) Accomplish the temporary preventive action specified in
paragraph 2.E. of the Accomplishment Instructions of the service
bulletin. Thereafter, repeat the inspection required by paragraph
(a) of this AD at intervals not to exceed 600 flight hours until the
requirements of paragraph (b) of this AD have been accomplished.
(b) Except as specified in paragraph (c) of this AD, within
3,000 flight hours after the effective date of this AD, install the
new staked bushings in the aileron actuation fitting in accordance
with Saab Service Bulletin 2000-57-014, Revision 02, dated February
11, 1997. Accomplishment of this installation terminates the
requirements of this AD.
(c) If, during the accomplishment of the installation required
by paragraph (a)(2)(i) or paragraph (b) of this AD, the diameter of
the small hole of the fitting lug is found to be outside the limits
specified in Saab Service Bulletin 2000-57-014, Revision 02, dated
February 11, 1997, repair it in accordance with a method approved by
the Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate.
(d) As of the effective date of this AD, no person shall install
on any airplane an aileron having part number, 7357995-843 (left-
hand) or 7357995-844 (right-hand), unless it has been modified in
accordance with paragraph (b) of this AD.
(e) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(f) 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.
Note 3: The subject of this AD is addressed in Swedish
airworthiness directive (SAD) 1-102R1, dated November 8, 1996.
Issued in Renton, Washington, on December 5, 1997.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-32424 Filed 12-10-97; 8:45 am]
BILLING CODE 4910-13-U
