[Federal Register Volume 64, Number 176 (Monday, September 13, 1999)]
[Proposed Rules]
[Pages 49418-49420]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-23743]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-200-AD]
RIN 2120-AA64
Airworthiness Directives; Sab Model SAAB SF340A and SAAB 340B
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 SF340A and
SAAB 340B series airplanes. This proposal would require repetitive
inspections of the control quadrant for loose screws, and replacement
of the control quadrant with a modified part, which constitutes
terminating action for the repetitive inspections. This proposal is
promoted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified by
the proposed AD are intended to prevent the power levers from binding
due to the backing out of screws that secure the solenoid bracket
within the flight idle stop assembly, which could result in the
malfunction of the flight idle stop mechanism and the inability to move
the power levers to flight idle.
DATES: Comments must be received by October 13, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-200-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: 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:
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 or 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
[[Page 49419]]
postcard on which the following statement is made: ``Comments to Docket
Number 99-NM-200-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, Tranport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 99-NM-200-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Luftfartsverket (LFV), which is the airworthiness authority for
Sweden, recently notified the FAA that an unsafe condition may exist on
certain Saab Model SAAB SF340A and SAAB 340B series airplanes. The LFV
advises that an operator has reported a problem with the left-hand
power lever binding and not going into reverse after landing. The
investigation showed that a screw had backed out of a cam and caused
binding within the control quadrant. Backing out of the screw has been
attributed to failure to apply locking compound during installation.
Another screw was also found to be missing locking compound. This
condition, if not corrected, could result in the malfunction of the
flight idle stop mechanism and the inability to move the power levers
to flight idle.
Explanation of Relevant Service Information
Saab has issued Service Bulletin 340-76-043, Revision 01, dated
July 29, 1999, which describes procedures for repetitive inspections of
the control quadrant for loose screws, and replacement of the control
quadrant with a modified control quadrant. Such replacement would
eliminate the need for the repetitive inspections. The 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. 1-143, dated July 2, 1999, in order to assure the
continued airworthiness of these airplanes in Sweden.
The Saab service bulletin references Adams Rite Aerospace Service
Letter General SL-01, dated April 6, 1999, as an additional source of
service information to accomplish the inspection.
FAA's Conclusions
These airplane models are manufactured in Sweden and are type
certificated for operation in the United States under the provisions of
section 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.
Cost Impact
The FAA estimates that 289 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 1 work
hour per airplane 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 AD on U.S. operators is estimated to be
$17,340, or $60 per airplane, per inspection cycle.
The FAA estimates that it would take approximately 4 work hours per
airplane to accomplish the proposed replacement, at an average labor
rate of $60 per work hour. Required parts would be supplied by the
parts manufacturer at no cost to the operators. Based on these figures,
the cost impact of the proposed replacement on U.S. operators is
estimated to be $69,360, or $240 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed 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 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 99-NM-200-AD.
Applicability: Saab Model SAAB SF340A series airplanes, serial
numbers 004 through 159 inclusive; and Model SAAB 340B series
airplanes, series number 160 through 459 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 (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 the power levers from binding due to the backing our
of screws that secure the solenoid bracket within the flight idle
stop assembly, which could result in the
[[Page 49420]]
malfunction of the flight idle stop mechanism and the inability to
move the power levers to flight idle, accomplish the following:
Inspection
(a) Within 800 flight hours after the effective date of this AD,
perform a borescopic inspection of the control quadrant for loose
screws, in accordance with Saab Service Bulletin 340-76-043,
Revision 01, dated July 29, 1999. If no loose screws are found,
repeat the inspection thereafter at intervals not to exceed 800
flight hours, until the requirements of paragraph (c) are
accomplished.
Note 2: Saab Service Bulletin 340-76-043, dated July 2, 1999,
references Adams Rite Aerospace Service Letter General SL-01, dated
April 6, 1999, as an additional source of service information to
accomplish the inspection.
Note 3: Inspections and replacements accomplished prior to the
effective date of this AD in accordance with Saab Service Bulletin
340-76-043, dated July 2, 1999, are considered acceptable for
compliance with the applicable action specified in this amendment.
Corrective Action
(b) If any loose screw is found during any inspection performed
in accordance with paragraph (a) of this AD, prior to further
flight, replace the exiting control quadrant with a modified control
quadrant in accordance with Saab Service Bulletin 340-76-043, dated
July 2, 1999.
Terminating Action
(c) Within 8,000 flight hours or 6 years after the effective
date of this AD, whichever occurs earlier: Replace the existing
control quadrant with a modified control quadrant in accordance with
Saab Service Bulletin 340-76-043, dated July 2, 1999. Such
replacement constitutes terminating action for the repetitive
inspections required by paragraph (a) of this AD.
Spares
(d) As of the effective date of this AD, no person shall
install, on any airplane, a control quadrant with a part number and
reference letter combination other than the following: part number
53082 and reference letter A
Alternative Methods of Compliance
(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, FAA,
Transport Airplane Directorate. Operations 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
(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 5: The subject of this AD is addressed in Swedish
airworthiness directive SAD No. 1-143, dated July 2, 1999.
Issued in Renton, Washington, on September 7, 1999.
D. L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-23743 Filed 9-10-99; 8:45 am]
BILLING CODE 4910-12-D
