[Federal Register Volume 65, Number 2 (Tuesday, January 4, 2000)]
[Rules and Regulations]
[Pages 209-211]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-9]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-200-AD; Amendment 39-11489; AD 99-27-08]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Saab Model SAAB SF340A and SAAB 340B series
airplanes, that requires 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 amendment is prompted by issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The actions specified by this 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
override function, and the inability to move the power levers aft of
flight idle.
DATES: Effective February 8, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 8, 2000.
ADDRESSES: The service information referenced in this AD may be
obtained from Saab Aircraft AB, SAAB Aircraft Product Support, S-
581.88, Linkoping, Sweden. This information may be examined at the
Federal Aviation Administration (FAA), Transport Airplane Directorate,
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Saab Model SAAB SF340A and
SAAB 340B series airplanes was published in the Federal Register on
September 13, 1999 (64 FR 49418). That action proposed to require
repetitive inspections of the control quadrant for loose screws, and
replacement of the control quadrant with a modified part, which would
terminate action for the repetitive inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Restatement of Unsafe Condition
One commenter, the manufacturer, requests that the proposed AD be
revised to restate the identified unsafe condition. The commenter
states that malfunction of the automatic flight idle
[[Page 210]]
stop mechanism would result in the inability to move the power levers
aft of flight idle, rather than ``to flight idle,'' as stated in the
proposed AD. The commenter also notes that, should the automatic system
fail, it can be overridden by the emergency override function. The
commenter suggests that pertinent sections of the AD be revised to read
``* * * could result in malfunction of the automatic flight idle stop
mechanism and the override function, preventing the power lever to be
moved aft of flight idle.'' The FAA concurs that the restatement
suggested by the commenter is a more accurate reflection of the unsafe
condition identified in this AD, and has revised the final rule
accordingly.
Revision of Corrective Action
The same commenter requests that paragraph (b) of the proposed AD
be revised to allow installation of an unmodified quadrant, provided it
has been inspected without discrepancies detected, and provided it is
subject to repetitive inspections until it has been modified. The
commenter states that it believes that an acceptable level of safety
can be maintained if these conditions are followed. This would allow a
quadrant other than a modified quadrant to be installed in the event
that loose screws are found in the installed quadrant during any
inspection required by paragraph (a) of the AD.
The FAA concurs that installation of any control quadrant that has
been modified, or that has been inspected in accordance with the
requirements of this AD and found to have no loose screws, is an
acceptable corrective action to address the identified unsafe
condition. The FAA has revised paragraph (b) of the AD to require such
action prior to further flight if loose screws are found in a control
quadrant. The FAA also has revised paragraph (d) of the AD, which
addresses installation of spare quadrants, to require such action for
any control quadrant prior to installation on any airplane.
Revision of Spares Paragraph
The commenter also advises the FAA that the version of the proposed
AD that was published in the Federal Register omitted certain
information pertinent to paragraph (d) of the AD and should be
corrected. The commenter states that the list of combinations of
acceptable part numbers and reference letters is incorrect, and the
list is missing several combinations.
The FAA acknowledges the inadvertent typographical error identified
in the Federal Register version of the proposed AD. The omission
related to certain modified control quadrants acceptable for
installation on the airplane. However, as previously described,
paragraph (d) of the AD has been broadened to allow installation of
both modified and certain unmodified quadrants. Therefore, the list of
combinations of part numbers and reference letters is now omitted, and
further change to paragraph (d) of the AD is unnecessary.
Cost Estimate
The same commenter states that it believes an estimate of one work
hour for the inspection, as provided in the cost impact information of
the proposed AD, to be an overestimate. The FAA infers that the
commenter is requesting that the cost estimate be revised downward.
The FAA does not concur. The estimate of 1 work hour was obtained
by rounding upward from the referenced service bulletin's Manpower
estimate of 15 minutes. This practice is followed for simplicity in
cost estimating, and does not significantly affect the total cost to
operators. No change to the AD is necessary.
Change to the Proposed AD
Paragraph (a) of the proposed AD cites Saab Service Bulletin 340-
76-043, Revision 01, dated July 29, 1999, as the appropriate source of
service information. However, reference to this revision was
inadvertently omitted from paragraphs (b) and (c) of the proposed AD.
The procedures described in Revision 01 of the service bulletin are
identical to those contained in the original issue of the service
bulletin, dated July 2, 1999; and Note 3 in the AD gives credit to
operators that may have previously accomplished required actions in
accordance with the original version. The FAA has revised paragraphs
(b) and (c) of the AD to reference Revision 01 of the service bulletin.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 289 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 1 work hour per
airplane to accomplish the required inspection, and that the average
labor rate is $60 per work hour. Based on these figures, the cost
impact of the required inspection on U.S. operators is estimated to be
$17,340, or $60 per airplane, per inspection cycle.
The FAA estimates that it will take approximately 4 work hours per
airplane to accomplish the required replacement, at an average labor
rate of $60 per work hour. Required parts will be supplied by the parts
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the required 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 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 adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
[[Page 211]]
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:
99-27-08 SAAB Aircraft AB: Amendment 39-11489. Docket 99-NM-200-AD.
Applicability: 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 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 override function, and the inability to
move the power levers aft of 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 existing control quadrant with a modified
control quadrant, or with a serviceable control quadrant that has
been inspected and found to have no loose screws, in accordance with
Saab Service Bulletin 340-76-043, Revision 01, dated July 29, 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, Revision 01, dated July 29, 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
a control quadrant on any airplane, unless the quadrant has been
modified, or has been inspected and found to have no loose screws,
in accordance with the requirements of this AD.
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. 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 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.
Incorporation by Reference
(g) The actions shall be done in accordance with Saab Service
Bulletin 340-76-043, Revision 01, dated July 29, 1999. This
incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be obtained from Saab Aircraft AB, SAAB Aircraft
Product Support, S-581.88, Linkoping, Sweden. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Note 5: The subject of this AD is addressed in Swedish
airworthiness directive SAD No. 1-143, dated July 2, 1999.
(h) This amendment becomes effective on February 8, 2000.
Issued in Renton, Washington, on December 23, 1999.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-9 Filed 1-3-00; 8:45 am]
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