[Federal Register Volume 63, Number 26 (Monday, February 9, 1998)]
[Proposed Rules]
[Pages 6499-6501]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3129]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-151-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 inspections
for excessive wear of the aileron control cables, cable guides, and
cable pulleys located at the rear wing spars, and corrective actions,
if necessary. This proposal also would require repetitive replacement
of the control cables and cable guides with new or serviceable
components. This proposal is prompted by the issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The actions specified by the proposed AD are intended to
detect and correct excessive wear on the aileron control cables, cable
guides, and cable pulleys located at the rear wing spars, which could
result in broken aileron control cables and consequent reduced
controllability of the airplane.
DATES: Comments must be received by March 11, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-151-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 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-151-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. 97-NM-151-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 it has
received reports of excessive wear of the aileron control cables at the
positions of the cable guides located at the rear wing spars. The cause
of this wear has been attributed to chafing that occurred between the
cables and the cable guides. Such wear, if not detected and corrected
in a timely manner, could result in broken aileron control cables and
consequent reduced controllability of the airplane.
Explanation of Relevant Service Information
Saab has issued Service Bulletin 2000-27-033, dated April 29, 1997,
which describes procedures for repetitive inspections for excessive
wear of the aileron control cables, cable guides, and cable pulleys
located at the rear wing spars, and corrective actions, if necessary.
These corrective actions include replacement of discrepant cables,
cable guides, and pulleys with serviceable parts; and rotation of the
cable pulleys to ensure that the bearings are not damaged. The service
bulletin also describes procedures for repetitive replacement of the
control cables and cable guides with new or serviceable control cables
and cable guides. The LFV classified this service bulletin as mandatory
and issued Swedish airworthiness directive SAD No. 1-111, dated April
30, 1997, 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.
[[Page 6500]]
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.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Cost Impact
The FAA estimates that 3 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 1 work hour per airplane to accomplish
the proposed inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the proposed inspection
required by this AD on U.S. operators is estimated to be $180, or $60
per airplane, per inspection cycle.
It would take approximately 8 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 manufacturer at no cost
to the operators. Based on these figures, the cost impact of the
proposed replacement required by this AD on U.S. operators is estimated
to be $1,440, or $480 per airplane, per replacement.
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 97-NM-151-AD.
Applicability: Model 2000 series airplanes, serial numbers 004
through 059 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 (c) 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 detect and correct excessive wear of the aileron control
cables, cable guides, and cable pulleys located at the rear wing
spars, which could result in broken aileron control cables and
consequent reduced controllability of the airplane, accomplish the
following:
(a) Inspect to detect discrepancies of the left- and right-hand
aileron control cables, cable guides, and cable pulleys at the time
specified in paragraph (a)(1) or (a)(2) of this AD, as applicable,
in accordance with Saab Service Bulletin 2000-27-033, dated April
29, 1997. Repeat the inspection thereafter at intervals not to
exceed 500 flight hours. If any discrepancy is found during any
inspection required by this AD, prior to further flight, perform
corrective action in accordance with the service bulletin.
(1) For airplanes on which Saab Modification 5784 has been
installed: Inspect at the later of the times specified in paragraphs
(a)(1)(i) and (a)(1)(ii) of this AD.
(i) Prior to the accumulation of 1,800 total flight hours; or
within 1,800 flight hours after accomplishment of the modification
or replacement of any control cable; whichever occurs latest. Or
(ii) Within 200 flight hours after the effective date of this
AD.
(2) For airplanes on which Saab Modification 5784 has not been
installed: Inspect at the later of the times specified in paragraphs
(a)(2)(i) and (a)(2)(ii) of this AD.
(i) Prior to the accumulation of 3,200 total flight hours, or
within 3,200 flight hours after replacement of any control cable,
whichever occurs later. Or
(ii) Within 200 flight hours after the effective date of this
AD.
Note 2: Although the inspection schedules of this AD apply to
both left- and right-hand wing cable systems, replacement of the
cable, guide, or pulley on one wing only, prior to scheduled
replacement, would result in subsequent staggered inspections for
the components of the left- and right-hand cable systems.
(b) Replace the aileron control cables, cable guides, and cable
pulleys with new or serviceable parts, as applicable; at the time
specified in paragraph (b)(1) or (b)(2) of this AD, as applicable;
in accordance with Saab Service Bulletin 2000-27-033, dated April
29, 1997.
(1) For airplanes on which Saab Modification 5784 has been
installed: Replace at the later of the times specified in paragraphs
(b)(1)(i) and (b)(1)(ii) of this AD. Thereafter, repeat the
inspection required by paragraph (a) of this AD at the time
specified in paragraph (a)(1); and replace the control cables and
cable guides thereafter prior to the accumulation of 3,200 flight
hours after replacement of any control cable.
(i) Prior to the accumulation of 3,200 total flight hours; or
within 3,200 flight hours after installation of the modification, or
after replacement of any control cable; whichever occurs latest. Or
(ii) Within 200 flight hours after the effective date of this
AD.
(2) For airplanes on which Modification 5784 has not been
installed: Replace at the later of the times specified in paragraphs
(b)(2)(i) and (b)(2)(ii) of this AD. Thereafter, repeat the
inspections required by paragraph (a) of this AD at the time
specified in paragraph (a)(2); and replace the control cables and
cable guides thereafter prior to the accumulation of 6,200 flight
hours following replacement of any control cable.
(i) Prior to the accumulation of 6,200 total flight hours, or
within 6,200 flight hours after replacement of any control cable,
whichever occurs later. Or
(ii) Within 200 flight hours after the effective date of this
AD.
(c) An alternative method of compliance or adjustment of the
compliance time that
[[Page 6501]]
provides an acceptable level of safety may be used if approved by
the Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate. 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(d) 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 4: The subject of this AD is addressed in Swedish
airworthiness directive SAD No. 1-111, dated April 30, 1997.
Issued in Renton, Washington, on February 2, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-3129 Filed 2-6-98; 8:45 am]
BILLING CODE 4910-13-U
