[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