Airworthiness Directives; Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B Airplanes, 52992-52994 [E6-14690]
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52992
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
Repair
(f) Within 12 months after the effective
date of this AD, repair the force link
assembly wire harness by doing all actions
specified in the Accomplishment
Instructions of the applicable service
information identified in Table 2 of this AD,
except as required by paragraph (g) of this
AD.
TABLE 2.—SERVICE INFORMATION
TABLE 3.—MATERIAL INCORPORATED
BY REFERENCE
For Model—
Use—
GV–SP series
airplanes.
Gulfstream G500 Customer
Bulletin 14, dated June 23,
2005.
Gulfstream G550 Customer
Bulletin 14, dated June 23,
2005.
Gulfstream GV Customer
Bulletin 135, dated June
23, 2005.
GV–SP series
airplanes.
GV series airplanes.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Note 1: The Gulfstream customer bulletins
identified in Table 2 of this AD include
Vought Service Bulletin SB–VAIGV/GVSP–
27–PG0098, dated May 9, 2005, as an
additional source of service information for
the repair.
Customer bulletin
Date
Gulfstream G500 Customer
Bulletin 14.
Gulfstream G550 Customer
Bulletin 14.
Gulfstream GV Customer
Bulletin 135.
June 23,
2005.
June 23,
2005.
June 23,
2005.
Issued in Renton, Washington, on August
28, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–14688 Filed 9–7–06; 8:45 am]
BILLING CODE 4910–13–P
Exception to Service Bulletin Specifications
(g) During the inspection of the
environmental seal around the installed
wires required by paragraph (f) of this AD: If
any nick or other damage is found, repair
before further flight using a method approved
by the Manager, Atlanta Aircraft Certification
Office (ACO), FAA. For a repair method to
be approved by the Manager, Atlanta ACO,
as required by this paragraph, the Manager’s
approval letter must specifically refer to this
AD.
rwilkins on PROD1PC63 with RULES
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Atlanta ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Material Incorporated by Reference
(i) You must use the service information
identified in Table 3 of this AD to perform
the actions that are required by this AD,
unless the AD specifies otherwise. Each
Gulfstream customer bulletin listed in Table
3 of this AD includes Vought Aircraft
Industries Service Bulletin SB–VAIGV/
GVSP–27–PG0098, dated May 9, 2005. The
Director of the Federal Register approved the
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Gulfstream
Aerospace Corporation, Technical
Publications Dept., P.O. Box 2206, Savannah,
Georgia 31402–2206, for a copy of this
service information. You may review copies
at the Docket Management Facility, U.S.
VerDate Aug<31>2005
17:41 Sep 07, 2006
Jkt 208001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003–NM–114–AD; Amendment
39–14751; AD 2006–18–12]
RIN 2120–AA64
Airworthiness Directives; Saab Model
SAAB-Fairchild SF340A (SAAB/
SF340A) and SAAB 340B Airplanes
SUMMARY: This amendment adopts a
new airworthiness directive (AD),
applicable to certain Saab Model SAABFairchild SF340A (SAAB/SF340A) and
SAAB 340B airplanes, that requires
modification and repetitive inspections
of the hot detection system of the tail
pipe harness of the engine nacelles. The
actions specified by this AD are
intended to prevent false warning
indications to the flightcrew from the
hot detection system due to
discrepancies of the harness, which
could result in an unnecessary aborted
takeoff on the ground or in-flight engine
shutdowns. This action is intended to
address the identified unsafe condition.
DATES: Effective October 13, 2006.
The incorporation by reference of a
certain publication listed in the
regulations is approved by the Director
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Sfmt 4700
FOR FURTHER INFORMATION CONTACT:
Mike Borfitz, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2677; 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-Fairchild SF340A (SAAB/
SF340A) and SAAB 340B airplanes was
published as a supplemental notice of
proposed rulemaking (NPRM) in the
Federal Register on June 26, 2006 (71
FR 36252). That action proposed to
require modification and repetitive
inspections of the hot detection system
of the tail pipe harness of the engine
nacelles.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the supplemental NPRM
or on the determination of the cost to
the public.
Conclusion
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
PO 00000
of the Federal Register as of October 13,
2006.
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.
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed in the
supplemental NPRM.
Cost Impact
We estimate that 280 airplanes of U.S.
registry will be affected by this AD.
It will take about 10 work hours per
airplane to accomplish the modification,
at an average labor rate of $80 per work
hour. Required parts cost will be
between $218 and $2,253. Based on
these figures, the cost impact of the
modification on U.S. operators is
estimated to be between $285,040 and
$854,840, or between $1,018 and $3,053
per airplane.
It will take about 1 work hour per
airplane to accomplish the inspection
and application of sealant, at an average
labor rate of $80 per work hour. Based
on these figures, the cost impact of this
E:\FR\FM\08SER1.SGM
08SER1
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
contained in the Rules Docket. A copy
of it may be obtained from the Rules
Docket at the location provided under
the caption ADDRESSES.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
rwilkins on PROD1PC63 with RULES
action on U.S. operators is estimated to
be $22,400, or $80 per airplane, per
inspection cycle.
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. 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.
I
Regulatory Impact
The regulations adopted herein will
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 final rule does not
have federalism implications under
Executive Order 13132.
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
VerDate Aug<31>2005
17:41 Sep 07, 2006
Jkt 208001
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:
I
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.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
the following new airworthiness
directive:
I
2006–18–12 Saab Aircraft AB: Amendment
39–14751. Docket 2003–NM–114–AD.
Applicability
Model SAAB-Fairchild SF340A (SAAB/
SF340A) airplanes, serial numbers –004
through –159 inclusive, and SAAB 340B
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
flightcrew from the hot detection system of
the tail pipe harness of the engine nacelles
due to discrepancies of the harness, which
could result in an unnecessary aborted
takeoff on the ground or in-flight engine
shutdowns, accomplish the following:
Modification/Repetitive Inspections
(a) Within 12 months 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,
thixotropic sealant, and connectors for
damage and/or corrosion, and all applicable
repairs), by doing all the actions specified in
the Accomplishment Instructions of Saab
Service Bulletin 340–26–030, Revision 01,
dated November 14, 2003. All applicable
repairs must be done before further flight in
accordance with the service bulletin. Repeat
the general visual inspection thereafter at
intervals not to exceed 12 months.
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
PO 00000
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52993
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) Accomplishing the modification/
repetitive inspections specified in Saab
Service Bulletin 340–26–030, dated October
28, 2002; or 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.
Reporting Requirement
(c) Within 30 days after any false warning
indication to the flightcrew from the hot
detection system of the tail pipe harness of
the engine nacelles occurs: Submit a report
containing the information specified in
paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of
this AD to the Swedish Civil Aviation
Authority (Luftfartsstyrelsen)—Attn: Mr.
Christer Sundqvist, SAAB 340 Certification
¨
Manager, SE–601 79, Norrkoping, Sweden.
Under the provisions of the Paperwork
Reduction Act (44 U.S.C. 3501 et seq.), the
Office of Management and Budget (OMB) has
approved the information collection
requirements contained in this AD and has
assigned OMB Control Number 2120–0056.
(1) The date and time, weather conditions,
and phase of flight of the warning.
(2) The action taken by the flightcrew to
address the warning (aborted takeoff, high
speed/high energy abort requiring inspection,
return for landing, in-flight diversion,
declared emergency, air traffic control (ATC)
priority handling requested or given, or
engine shutdown).
(3) The action taken by maintenance to
address/correct the warning.
(4) Time-in-service on the airplane since
the last inspection accomplished in
accordance with paragraph (a) of this AD.
Alternative Methods of Compliance
(AMOCs)
(d)(1) In accordance with 14 CFR 39.19, the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, is
authorized to approve AMOCs for this AD.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
Note 2: The subject of this AD is addressed
in Swedish airworthiness directive 1–184,
effective October 28, 2002.
Incorporation by Reference
(e) Unless otherwise specified in this AD,
the actions must be done in accordance with
Saab Service Bulletin 340–26–030, Revision
01, dated November 14, 2003. 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. To get copies of this service
information, contact Saab Aircraft AB, SAAB
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08SER1
52994
Federal Register / Vol. 71, No. 174 / Friday, September 8, 2006 / Rules and Regulations
Aircraft Product Support, S–581.88,
¨
Linkoping, Sweden. To inspect copies of this
service information, go to the FAA, Transport
Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at the NARA, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Effective Date
(f) This amendment becomes effective on
October 13, 2006.
Issued in Renton, Washington, on August
28, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–14690 Filed 9–7–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25244; Directorate
Identifier 2006–NE–25–AD; Amendment 39–
14754; AD 2006–18–15]
RIN 2120–AA64
Airworthiness Directives; Hartzell
Propeller Inc. ( )HC–( )2Y( )–( ) Series
Propellers
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
rwilkins on PROD1PC63 with RULES
AGENCY:
19:28 Sep 07, 2006
Jkt 208001
Use one of the following
addresses to comment on this AD:
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Hartzell Propeller Inc.
Technical Publications Department, One
Propeller Place, Piqua, OH 45356;
telephone (937) 778–4200; fax (937)
778–4391, for the service information
identified in this AD.
ADDRESSES:
Tim
Smyth, Aerospace Engineer, Chicago
Aircraft Certification Office, FAA, Small
Airplane Directorate, 2300 East Devon
Avenue, Des Plaines, IL 60018–4696;
telephone (847) 294–7132; fax (847)
294–7834.
FOR FURTHER INFORMATION CONTACT:
In April
2006, we received a report of a propeller
blade separation on a Hartzell Propeller
Inc. two blade, aluminum hub,
‘‘compact’’ ( )HC–( )2Y( )–( ) series
propeller. Also, to date, we received
seven reports of excessive vibration
determined to be caused by cracks in
the propeller hub fillet. Those
propellers were manufactured before
December 1991 (non-suffix SN propeller
hubs) and are installed on Lycoming O–
, IO–, LO–, and AEIO–360 series
reciprocating engines. This condition, if
not corrected, could result in blade
separation and subsequent loss of
airplane control.
SUPPLEMENTARY INFORMATION:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Hartzell
Propeller Inc. ( )HC–( )2Y( )–( ) series
propellers with non-suffix serial number
(SN) propeller hubs installed on
Lycoming O–, IO–, LO–, and AEIO–360
series reciprocating engines. This AD
requires initial and repetitive eddy
current inspections (ECI) of the front
cylinder half of the propeller hub for
cracks and removing cracked hubs from
service before further flight. In addition,
this AD allows installation of an
improved design propeller hub (suffix
SN ‘‘A’’ or ‘‘B’’) as terminating action to
the repetitive ECI. This AD results from
a report of a propeller blade separating
from a propeller hub. We are issuing
this AD to prevent failure of the
propeller hub causing blade separation
and subsequent loss of airplane control.
DATES: This AD becomes effective
September 25, 2006. The Director of the
Federal Register approved the
incorporation by reference of certain
VerDate Aug<31>2005
publications listed in the regulations as
of September 25, 2006.
We must receive any comments on
this AD by November 7, 2006.
Relevant Service Information
We have reviewed and approved the
technical contents of Hartzell Propeller
Inc. Service Bulletin (SB) HC–SB–61–
269, dated April 18, 2005. That SB
describes procedures for eddy current
inspections of propeller hubs on
affected propellers. That SB also lists
improved design replacement propeller
hub part numbers.
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other Hartzell Propeller Inc. ( )HC–
( )2Y( )–( ) series propellers of the
same type design. For that reason, we
are issuing this AD to prevent failure of
the propeller hub causing blade
separation and subsequent loss of
airplane control. This AD requires,
within 50 operating hours time-inservice (TIS), an initial ECI of the front
cylinder half of non-suffix SN propeller
hubs for cracks. This AD also requires,
within every 100 operating hours TIS or
annual inspection, whichever occurs
first, repetitive ECIs of the front cylinder
half of non-suffix SN propeller hubs for
cracks. This AD also requires removing
cracked hubs from service before further
flight. You must use the service
information described previously to
perform the actions required by this AD.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2006–25244; Directorate Identifier
2006–NE–25–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of the DMS Web site,
anyone can find and read the comments
in any of our dockets, including the
name of the individual who sent the
comment (or signed the comment on
behalf of an association, business, labor
union, etc.). You may review the DOT’s
complete Privacy Act Statement in the
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]]>Agencies
[Federal Register Volume 71, Number 174 (Friday, September 8, 2006)]
[Rules and Regulations]
[Pages 52992-52994]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-14690]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-114-AD; Amendment 39-14751; AD 2006-18-12]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB-Fairchild SF340A (SAAB/
SF340A) and SAAB 340B Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Saab Model SAAB-Fairchild SF340A (SAAB/SF340A)
and SAAB 340B airplanes, that requires modification and repetitive
inspections of the hot detection system of the tail pipe harness of the
engine nacelles. The actions specified by this AD are intended to
prevent false warning indications to the flightcrew from the hot
detection system due to discrepancies of the harness, which could
result in an unnecessary aborted takeoff on the ground or in-flight
engine shutdowns. This action is intended to address the identified
unsafe condition.
DATES: Effective October 13, 2006.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of October 13, 2006.
ADDRESSES: The service information referenced in this AD 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
Federal Aviation Administration (FAA), Transport Airplane Directorate,
Rules Docket, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Mike Borfitz, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2677; 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-Fairchild
SF340A (SAAB/SF340A) and SAAB 340B airplanes was published as a
supplemental notice of proposed rulemaking (NPRM) in the Federal
Register on June 26, 2006 (71 FR 36252). That action proposed to
require modification and repetitive inspections of the hot detection
system of the tail pipe harness of the engine nacelles.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the supplemental
NPRM or on the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
in the supplemental NPRM.
Cost Impact
We estimate that 280 airplanes of U.S. registry will be affected by
this AD.
It will take about 10 work hours per airplane to accomplish the
modification, at an average labor rate of $80 per work hour. Required
parts cost will be between $218 and $2,253. Based on these figures, the
cost impact of the modification on U.S. operators is estimated to be
between $285,040 and $854,840, or between $1,018 and $3,053 per
airplane.
It will take about 1 work hour per airplane to accomplish the
inspection and application of sealant, at an average labor rate of $80
per work hour. Based on these figures, the cost impact of this
[[Page 52993]]
action on U.S. operators is estimated to be $22,400, or $80 per
airplane, per inspection cycle.
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. 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.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Impact
The regulations adopted herein will 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 final rule does not have federalism
implications under Executive Order 13132.
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
0
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:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2006-18-12 Saab Aircraft AB: Amendment 39-14751. Docket 2003-NM-114-
AD.
Applicability
Model SAAB-Fairchild SF340A (SAAB/SF340A) airplanes, serial
numbers -004 through -159 inclusive, and SAAB 340B 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 flightcrew from the
hot detection system of the tail pipe harness of the engine nacelles
due to discrepancies of the harness, which could result in an
unnecessary aborted takeoff on the ground or in-flight engine
shutdowns, accomplish the following:
Modification/Repetitive Inspections
(a) Within 12 months 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, thixotropic sealant, and connectors for damage and/or
corrosion, and all applicable repairs), by doing all the actions
specified in the Accomplishment Instructions of Saab Service
Bulletin 340-26-030, Revision 01, dated November 14, 2003. All
applicable repairs must be done before further flight in accordance
with the service bulletin. Repeat the general visual inspection
thereafter at intervals not to exceed 12 months.
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) Accomplishing the modification/repetitive inspections
specified in Saab Service Bulletin 340-26-030, dated October 28,
2002; or 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.
Reporting Requirement
(c) Within 30 days after any false warning indication to the
flightcrew from the hot detection system of the tail pipe harness of
the engine nacelles occurs: Submit a report containing the
information specified in paragraphs (c)(1), (c)(2), (c)(3), and
(c)(4) of this AD to the Swedish Civil Aviation Authority
(Luftfartsstyrelsen)--Attn: Mr. Christer Sundqvist, SAAB 340
Certification Manager, SE-601 79, Norrk[ouml]ping, Sweden. Under the
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.),
the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
(1) The date and time, weather conditions, and phase of flight
of the warning.
(2) The action taken by the flightcrew to address the warning
(aborted takeoff, high speed/high energy abort requiring inspection,
return for landing, in-flight diversion, declared emergency, air
traffic control (ATC) priority handling requested or given, or
engine shutdown).
(3) The action taken by maintenance to address/correct the
warning.
(4) Time-in-service on the airplane since the last inspection
accomplished in accordance with paragraph (a) of this AD.
Alternative Methods of Compliance (AMOCs)
(d)(1) In accordance with 14 CFR 39.19, the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
is authorized to approve AMOCs for this AD.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Note 2: The subject of this AD is addressed in Swedish
airworthiness directive 1-184, effective October 28, 2002.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions must be
done in accordance with Saab Service Bulletin 340-26-030, Revision
01, dated November 14, 2003. 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. To get copies of this service
information, contact Saab Aircraft AB, SAAB
[[Page 52994]]
Aircraft Product Support, S-581.88, Link[ouml]ping, Sweden. To
inspect copies of this service information, go to the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or
to the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_
locations.html.
Effective Date
(f) This amendment becomes effective on October 13, 2006.
Issued in Renton, Washington, on August 28, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-14690 Filed 9-7-06; 8:45 am]
BILLING CODE 4910-13-P
