[Federal Register Volume 68, Number 210 (Thursday, October 30, 2003)]
[Proposed Rules]
[Pages 61774-61775]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-27321]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-146-AD]
RIN 2120-AA64


Airworthiness Directives; Saab 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 removing the 
two direct current (DC) over-voltage/feeder-fault test switches from 
the Test 2 Panel of the generator control unit, and follow-on actions. 
This action is necessary to prevent the loss of the DC generators, 
which could result in the loss of normal electrical power to the 
airplane and increased pilot workload. This action is intended to 
address the identified unsafe condition.

DATES: Comments must be received by December 1, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-146-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-146-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Saab Aircraft AB, SAAB Aircraft Product Support, S-
581.88, Link[ouml]ping, Sweden. This information may be examined at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Rosanne Ryburn, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2139; 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 action may be changed in 
light of the comments received.
    Submit comments using the following format:

[sbull] Organize comments issue by issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the proposed AD 
is being requested.
[sbull] Include justification (e.g., reasons or data) for each request.

    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-146-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-114, Attention: Rules 
Docket No. 2002-NM-146-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

[[Page 61775]]

Model SAAB SF340A, and SAAB 340B series airplanes. The LFV advises that 
it has received reports of the two direct current (DC) generators of 
the generator control unit (GCU) going off-line during a lightning 
strike, which could cause a malfunction of the DC over-voltage/feeder-
fault test switches. This malfunction can momentarily inhibit the reset 
capability of the GCU and prevent the generators from coming back on-
line. Loss of the DC generators could result in the loss of normal 
electrical power to the airplane and increased pilot workload.

Explanation of Relevant Service Information

    Saab has issued Service Bulletin 340-24-023, Revision 02, dated 
November 15, 2001, which describes procedures for removing the two DC 
over-voltage/feeder-fault test switches from the Test 2 Panel of the 
GCU, and follow-on actions. The follow-on actions include modifying 
certain associated wiring, attaching related test function wiring to 
the wire harness, installing a blanking plate on the Test 2 Panel, and 
operational testing. 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 1-169, dated November 20, 
2001, to ensure the continued airworthiness of these airplanes in 
Sweden.

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 251 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 4 work 
hours per airplane to accomplish the proposed actions, and that the 
average labor rate is $65 per work hour. Required parts would cost 
approximately $107 per airplane. Based on these figures, the cost 
impact of the proposed AD on U.S. operators is estimated to be $92,117, 
or $367 per airplane.
    The cost impact figure discussed above is 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. The cost impact figures 
discussed in AD rulemaking actions represent only the time necessary to 
perform the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations proposed herein would 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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 2002-NM-146-AD.

    Applicability: Model SAAB SF340A series airplanes having serial 
numbers 004 through 159 inclusive; and SAAB 340B series airplanes 
having serial numbers 160 through 379 inclusive; certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent the loss of the DC generators, which could result in 
the loss of normal electrical power to the airplane and increased 
pilot workload, accomplish the following:

Removal of DC Generator Test Switches

    (a) Within 5,000 flight hours or two years after the effective 
date of this AD, whichever occurs later: Remove the two DC over-
voltage/feeder-fault test switches from the Test 2 Panel of the 
generator control unit and do all the follow-on actions specified in 
the Accomplishment Instructions of Saab Service Bulletin 340-24-023, 
Revision 02, dated November 15, 2001. Do the actions per the service 
bulletin.

Alternative Methods of Compliance

    (b) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized 
to approve alternative methods of compliance for this AD.

    Note 1: The subject of this AD is addressed in Swedish 
airworthiness directive 1-169, dated November 20, 2001.


    Issued in Renton, Washington, on October 24, 2003.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-27321 Filed 10-29-03; 8:45 am]
BILLING CODE 4910-13-P