[Federal Register Volume 69, Number 63 (Thursday, April 1, 2004)]
[Proposed Rules]
[Pages 17101-17103]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-7302]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-114-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 modification of 
the hot detection system of the tail pipe harness of the engine 
nacelles. This action is necessary to prevent false warning indications 
to the flight crew from the hot detection system due to discrepancies 
of the harness, which could result in unnecessary aborted takeoffs on 
the ground or an in-flight engine shut down. This action is intended to 
address the identified unsafe condition.

DATES: Comments must be received by May 3, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-114-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. 2003-NM-114-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,

[[Page 17102]]

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:
     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.
     For each issue, state what specific change to 
the proposed AD is being requested.
     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 2003-NM-114-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. 2003-NM-114-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 SF340A and SAAB 340B series airplanes. The LFV advises 
that operators have reported false warning indications to the flight 
crew from the hot detection system of the tail pipe harness of the 
engine nacelles. The cause of the false warnings has been attributed to 
moisture ingress, corroded connectors, and chafed and broken wires of 
the hot detection harness of the tail pipe. Such false warnings have 
resulted in unnecessary aborted takeoffs on the ground and in-flight 
engine shut downs.

Explanation of Relevant Service Information

    Saab has issued Service Bulletin 340-26-030, dated October 28, 
2002, which describes procedures for modification of the hot detection 
harness, which include the following:
     A one-time inspection of the heat shrink sleeve, 
sealant, and connectors of the hot detection harness of the tail pipe 
for damage and/or corrosion, and repair if necessary.
     Installation of a new hot detection harness.
     Installation of new terminal lugs and shrinkable 
tube.
     Installation of sealant around the terminal lugs 
on the fire detectors.
    The service bulletin also describes procedures for an operational 
test of the fire detection system of the engine nacelles following 
accomplishment of the above actions.
    In addition, Service Bulletin 340-26-030 specifies that 
incorporation of the modifications specified in Saab Service Bulletins 
340-26-018, Revision 02, and 340-26-029, both dated October 28, 2002; 
meets the modification specified in the referenced service bulletin. 
These service bulletins describe modifications similar to the 
modification specified in the referenced service bulletin.
    Accomplishment of the actions specified in Service Bulletin 340-26-
030 is intended to adequately address the identified unsafe condition. 
The LFV classified this service bulletin as mandatory and issued 
Swedish airworthiness directive 1-184, dated October 28, 2002, 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 us informed of the 
situation described above. We have 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 Service Bulletin 340-26-030, except as 
discussed below.

Difference Between Service Bulletin and This Proposed AD

    The referenced service bulletin refers only to an ``inspection'' 
for damage and/or corrosion of the heat shrink sleeve, sealant, and 
connectors of the hot detection harness of the tail pipe. We have 
determined that the procedures in the referenced service bulletin 
should be described as a ``general visual inspection.'' Note 1 has been 
included in this proposed AD to define this type of inspection.

Cost Impact

    The FAA estimates that 280 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take about 10 work hours 
per airplane to accomplish the proposed modification, and that the 
average labor rate is $65 per work hour. Required parts would be free 
of charge. Based on these figures, the cost impact of the proposed 
modification on U.S. operators is estimated to be $182,000, or $650 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

[[Page 17103]]

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 2003-NM-114-AD.

    Applicability: Model SAAB SF340A series airplanes, serial 
numbers -004 through -159 inclusive, and SAAB 340B series airplanes, 
serial numbers -160 through -459 inclusive, certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent false warning indications to the flight crew from the 
hot detection system of the tail pipe harness of the engine nacelles 
due to discrepancies of the harness, which could result in 
unnecessary aborted takeoffs on the ground or an in-flight engine 
shut down, accomplish the following:

Modification

    (a) Within one year after the effective date of this AD: Modify 
the hot detection system of the tail pipe harness of the engine 
nacelles (including a general visual inspection of the heat shrink 
sleeve, sealant, and connectors for damage and/or corrosion, and any 
applicable repair), by doing all the actions per Parts 2.A. through 
2.I. inclusive of the Accomplishment Instructions of Saab Service 
Bulletin 340-26-030, dated October 28, 2002. Any applicable repair 
must be done before further flight.

    Note 1: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

    (b) Accomplishment of the modifications specified in Saab 
Service Bulletins 340-26-018, Revision 02, and 340-26-029, both 
dated October 28, 2002; before the effective date of this AD, is 
considered acceptable for compliance with the modification required 
by paragraph (a) of this AD.

Alternative Methods of Compliance

    (c) 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 2: The subject of this AD is addressed in Swedish 
airworthiness directive 1-184, dated October 28, 2002.


    Issued in Renton, Washington, on March 26, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-7302 Filed 3-31-04; 8:45 am]
BILLING CODE 4910-13-P