Airworthiness Directives; Saab Model SAAB 2000 Series Airplanes, 18275-18277 [05-6915]
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Federal Register / Vol. 70, No. 68 / Monday, April 11, 2005 / Rules and Regulations
PART 39—AIRWORTHINESS
DIRECTIVES
the compliance times specified unless the
actions have already been done.
1. The authority citation for part 39
continues to read as follows:
Initial Visual Inspection
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–11889 (65 FR
58177, September 27, 2000) and by
adding a new airworthiness directive,
Amendment 39–14052, to read as
follows:
I
2005–07–27 Aviointeriors S.p.A. (formerly
ALVEN): Amendment 39–14052. Docket
No. 2000–NE–09–AD.
Effective Date
(a) This AD becomes effective May 16,
2005.
Affected ADs
(b) This AD supersedes AD 2000–18–04.
Applicability
(c) This AD applies to Aviointeriors S.p.A.
(formerly ALVEN), model 312 seats. These
seats are installed in, but not limited to,
Fokker Model F27 Mark 050, Mark 500, and
Mark 600 airplanes.
Unsafe Condition
(d) This AD results from reports of 88
cracked seat central crossmembers and 60
aisle side crossmembers, to date; and, from
the introduction of reinforced optional seat
crossmembers by the manufacturer. The
actions specified in this AD are intended to
prevent the loss of the structural integrity of
the seat due to cracks in seat crossmembers,
which could lead to passenger injury.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
(f) Perform an initial visual inspection of
the crossmember for cracks, within 12,000
hours time-in-service (TIS); or within 180
days after the effective date of this AD if the
crossmember has more than 12,000 hours
TIS, as follows:
(1) Inspect seat central crossmembers, part
number (P/N) DM03437–1, using Section 2.
of Inspection Procedure of Aviointeriors
Service Bulletin (SB) No. 312/912–01,
Revision 2, dated August 1, 2000.
(2) Replace any cracked central
crossmember with a new crossmember of the
same P/N. Use Section 3. Crossmember
Replacement Procedure, Steps 3.1 though
3.10 of Aviointeriors SB No. 312/912–01,
Revision 2, dated August 1, 2000.
(3) Inspect seat aisle side crossmembers, P/
Ns DM03435–1, DM03435–2, and DM03437–
1 (Disabled People seat application), using
Section 2. of Inspection Procedure of
Aviointeriors SB No. 312/912–02, Revision 1,
dated August 1, 2000.
(4) Replace any cracked aisle side
crossmember with a new crossmember of the
same P/N. Use Section 3. Crossmember
Replacement Procedure, Steps 3.1 though 3.8
of Aviointeriors SB No. 312/912–02, Revision
1, dated August 1, 2000.
Repetitive Visual Inspections
(g) Perform repetitive visual inspections of
crossmembers, P/N DM03435–1, DM03435–
2, and DM03437–1, for cracks, within 650
hours TIS after the last inspection. Use
paragraphs (f)(1) through (f)(4) of this AD to
inspect and disposition crossmembers.
Optional Terminating Action
(h) As optional terminating actions to the
repetitive inspections required by this AD, do
the following:
(1) Replace seat central crossmembers, P/
N DM03437–1, with reinforced
crossmembers, P/N F11541300000. Use
Section 2. Crossmember Replacement
Procedure, Steps 2.1 through 2.11 of
Aviointeriors SB No. 312/912–03, dated
August 1, 2000.
(2) Replace seat aisle side crossmembers,
P/N DM03435–1, DM03435–2, and
DM03437–1 (Disabled People seat
application), with reinforced crossmembers,
P/N F11555400000, F11555500000, and
F11541300000, respectively. Use Section 2.
Crossmember Replacement Procedure, Steps
2.1 through 2.11 of Aviointeriors SB No. 312/
912–04, dated August 1, 2000.
Alternative Methods of Compliance
(i) The Manager, Boston Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
Material Incorporated by Reference
(j) You must use the Aviointeriors service
information specified in Table 1 of this AD
to perform the inspections and replacements
required by this AD. The Director of the
Federal Register approved the incorporation
by reference of the documents in Table 1 of
this AD in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Contact Aviointeriors
S.p.A., Via Appia Km. 66.4—04013 Latina,
Italy; telephone: 39–0773–6891; fax: 39–
0773–631546, for a copy of this service
information. You can review copies at the
FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive
Park, Burlington, MA, or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html. Table 1 follows:
TABLE 1.—INCORPORATION BY REFERENCE
Aviointeriors service bulletin No.
312/912–01,
312/912–02,
312/912–03,
312/912–04,
Total
Total
Total
Total
Pages:
Pages:
Pages:
Pages:
8
9
8
8
Page
........................................................................................................
........................................................................................................
........................................................................................................
........................................................................................................
Related Information
Issued in Burlington, Massachusetts, on
April 1, 2005.
Diane Cook,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–6912 Filed 4–8–05; 8:45 am]
2 ...................
1 ...................
Original .........
Original .........
August
August
August
August
1,
1,
1,
1,
2000.
2000.
2000.
2000.
Final rule.
ACTION:
Federal Aviation Administration
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Saab Model SAAB 2000 series airplanes.
This AD requires a one-time inspection
to detect a broken terminal stud on a
main relay of the electrical power
generator, and corrective action if
necessary. This AD is prompted by
disconnection of an electrical power
generator during an inspection flight,
which was caused by a broken terminal
stud on the main relay. We are issuing
this AD to prevent a broken terminal
stud on the main relay of an electrical
14 CFR Part 39
[Docket No. FAA–2005–20244; Directorate
Identifier 2004–NM–204–AD; Amendment
39–14051; AD 2005–07–26]
RIN 2120–AA64
Airworthiness Directives; Saab Model
SAAB 2000 Series Airplanes
BILLING CODE 4910–13–P
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
16:26 Apr 08, 2005
...............
...............
...............
...............
Date
DEPARTMENT OF TRANSPORTATION
(k) Ente Nazionale per l’Aviazione Civile
airworthiness directives 2000–511 and 2000–
512, both dated November 7, 2000, also
address the subject of this AD.
VerDate jul<14>2003
ALL
ALL
ALL
ALL
Revision
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18276
Federal Register / Vol. 70, No. 68 / Monday, April 11, 2005 / Rules and Regulations
power generator, which could reduce
the redundancy of electrical power
systems, result in increased pilot
workload, and contribute to reduced
controllability of the airplane.
DATES: This AD becomes effective May
16, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of May 16, 2005.
ADDRESSES: For service information
identified in this AD, contact Saab
Aircraft AB, SAAB Aircraft Product
¨
Support, S–581.88, Linkoping, Sweden.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20244; the directorate
identifier for this docket is 2004–NM–
204–AD.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Saab Model SAAB
2000 series airplanes. That action,
published in the Federal Register on
February 1, 2005 (70 FR 5064), proposed
to require a one-time inspection to
detect a broken terminal stud on a main
relay of the electrical power generator,
and corrective action if necessary.
airplane, at an average labor rate of $65
per work hour. Based on these figures,
the estimated cost of the AD for U.S.
operators is $975, or $325 per airplane.
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 Findings
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been submitted on the proposed
AD or on the determination of the cost
to the public.
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD 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.
For the reasons discussed above, I
certify that this AD:
(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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
Conclusion
List of Subjects in 14 CFR Part 39
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Costs of Compliance
I
Comments
This AD will affect about 3 airplanes
of U.S. registry. The required actions
will take about 5 work hours per
VerDate jul<14>2003
16:26 Apr 08, 2005
Jkt 205001
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2005–07–26 Saab Aircraft AB: Amendment
39–14051. Docket No. FAA–2005–20244;
Directorate Identifier 2004–NM–204–AD.
Effective Date
(a) This AD becomes effective May 16,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Saab Model SAAB
2000 series airplanes, certificated in any
category, serial numbers –004 through –063
inclusive.
Unsafe Condition
(d) This AD was prompted by
disconnection of an electrical power
generator during an inspection flight, which
was caused by a broken terminal stud on the
main relay. We are issuing this AD to prevent
a broken terminal stud on the main relay of
an electrical power generator, which could
reduce the redundancy of electrical power
systems, result in increased pilot workload,
and contribute to reduced controllability of
the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Inspection and Corrective Actions
(f) Within 6 months after the effective date
of this AD, perform a one-time general visual
inspection to detect a broken terminal stud
on a main relay of the electrical power
generator, and perform corrective actions as
applicable, by doing all of the actions in the
Accomplishment Instructions of Saab Service
Bulletin 2000–24–017, dated April 3, 2003.
Although the service bulletin specifies to
submit certain information to the
manufacturer, this AD does not include that
requirement.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘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 ensure visual access to
all 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.’’
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Federal Register / Vol. 70, No. 68 / Monday, April 11, 2005 / Rules and Regulations
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(h) Swedish airworthiness directive 1–190,
dated April 4, 2003, also addresses the
subject of this AD.
Material Incorporated by Reference
(i) You must use Saab Service Bulletin
2000–24–017, dated April 3, 2003, to perform
the actions that are required by this AD,
unless the AD specifies otherwise. The
Director of the Federal Register approves the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get copies of the service
information, contact Saab Aircraft AB, SAAB
Aircraft Product Support, S–581.88,
¨
Linkoping, Sweden. To view the AD docket,
contact the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., Room PL–401, Nassif Building,
Washington, DC. To review copies of the
service information, contact 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.
Issued in Renton, Washington, on March
31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–6915 Filed 4–8–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001–NM–181–AD; Amendment
39–14046; AD 2005–07–21]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–200F and –200C Series
Airplanes
Federal Aviation
Administration, Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment supersedes
an existing airworthiness directive (AD),
applicable to all Boeing Model 747–
200F and –200C series airplanes, that
currently requires repetitive detailed
inspections or a one-time open-hole
high frequency eddy current inspection
to detect cracking of certain areas of the
upper deck floor beams, and corrective
VerDate jul<14>2003
16:26 Apr 08, 2005
Jkt 205001
actions if necessary. This amendment
requires new one-time inspections for
cracking of the web, upper chord, and
strap of the upper deck floor beams.
This action also requires modifying or
repairing the upper deck floor beams, as
applicable, which eventually
necessitates accomplishment of new
repetitive inspections for cracking of the
upper deck floor beams. The actions
specified by this AD are intended to
prevent fatigue cracks in the upper
chord and web of upper deck floor
beams and the resultant failure of such
floor beams. Failure of a floor beam
could result in damage to critical flight
control cables and wire bundles that
pass through the floor beam, and
consequent loss of controllability of the
airplane. Failure of the floor beam also
could result in the failure of the
adjacent fuselage frames and skin, and
consequent rapid decompression of the
airplane. This action is intended to
address the identified unsafe condition.
DATES: Effective May 16, 2005.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of May 16,
2005.
The incorporation by reference of
Boeing Alert Service Bulletin 747–
53A2420, dated March 26, 1998, as
listed in the regulations, was approved
previously by the Director of the Federal
Register as of May 11, 1998 (63 FR
20311, April 24, 1998).
ADDRESSES: The service information
referenced in this AD may be obtained
from Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington
98124–2207. 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: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: A
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39)
by superseding AD 98–09–17,
amendment 39–10498 (63 FR 20311,
April 24, 1998); which is applicable to
all Boeing Model 747–200F and –200C
series airplanes; was published in the
Federal Register on June 18, 2003 (68
FR 36510). The action proposed to
continue to require repetitive detailed
inspections or a one-time open-hole
high frequency eddy current inspection
PO 00000
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18277
to detect cracking of certain areas of the
upper deck floor beams, and corrective
actions if necessary. The action also
proposed to require new one-time
inspections for cracking of the web,
upper chord, and strap of the upper
deck floor beams. The action also
proposed to require modification or
repair of the upper deck floor beams, as
applicable, which would eventually
necessitate accomplishment of new
repetitive inspections for cracking of the
upper deck floor beams.
Comments
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. The FAA
has duly considered the comments
received.
Request To Allow Modification/Repair
Per Service Bulletin
One commenter, the airplane
manufacturer, requests that we revise
paragraphs (g) and (h)(2) of the
proposed AD to allow modification and
permanent repairs to be accomplished
in accordance with Boeing Alert Service
Bulletin 747–53A2429, dated March 22,
2001. The same commenter also
requests that Notes 4 and 5 be removed
from the proposed AD. (Those notes
state that the procedures for the
modification and permanent repair
specified in Boeing Alert Service
Bulletin 747–53A2429 do not provide
an adequate level of safety.) The
commenter states that the procedures in
the service bulletin for the modification
and permanent repair are adequate. The
commenter acknowledges, however,
that analysis has shown that additional
inspection locations should be added to
the post-modification/repair program.
The commenter notes that the service
bulletin will be revised in the future to
include additional inspection
procedures.
We partially concur with the
commenter’s request. As we explain in
the ‘‘Differences Between Proposed AD
and Service Bulletins’’ section of the
proposed AD, the procedures for the
modification and permanent repair
stated in the original issue of Boeing
Alert Service Bulletin 747–53A2429 do
not provide an adequate level of safety.
This determination is based on reports
that cracking has been found on
airplanes that have a modification
similar to that described in Boeing Alert
Service Bulletin 747–53A2429.
However, we do agree that the
procedures for the modification and
permanent repair specified in Boeing
Alert Service Bulletin 747–53A2429
would be acceptable if additional postmodification/repair inspections are
E:\FR\FM\11APR1.SGM
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]]>Agencies
[Federal Register Volume 70, Number 68 (Monday, April 11, 2005)]
[Rules and Regulations]
[Pages 18275-18277]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6915]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20244; Directorate Identifier 2004-NM-204-AD;
Amendment 39-14051; AD 2005-07-26]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB 2000 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Saab Model SAAB 2000 series airplanes. This AD requires a one-
time inspection to detect a broken terminal stud on a main relay of the
electrical power generator, and corrective action if necessary. This AD
is prompted by disconnection of an electrical power generator during an
inspection flight, which was caused by a broken terminal stud on the
main relay. We are issuing this AD to prevent a broken terminal stud on
the main relay of an electrical
[[Page 18276]]
power generator, which could reduce the redundancy of electrical power
systems, result in increased pilot workload, and contribute to reduced
controllability of the airplane.
DATES: This AD becomes effective May 16, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of May
16, 2005.
ADDRESSES: For service information identified in this AD, contact Saab
Aircraft AB, SAAB Aircraft Product Support, S-581.88, Link[ouml]ping,
Sweden.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Washington, DC. This docket number is FAA-2005-20244; the directorate
identifier for this docket is 2004-NM-204-AD.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for certain Saab Model SAAB 2000 series airplanes. That
action, published in the Federal Register on February 1, 2005 (70 FR
5064), proposed to require a one-time inspection to detect a broken
terminal stud on a main relay of the electrical power generator, and
corrective action if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been submitted on the proposed
AD 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.
Costs of Compliance
This AD will affect about 3 airplanes of U.S. registry. The
required actions will take about 5 work hours per airplane, at an
average labor rate of $65 per work hour. Based on these figures, the
estimated cost of the AD for U.S. operators is $975, or $325 per
airplane.
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 Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2005-07-26 Saab Aircraft AB: Amendment 39-14051. Docket No. FAA-
2005-20244; Directorate Identifier 2004-NM-204-AD.
Effective Date
(a) This AD becomes effective May 16, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Saab Model SAAB 2000 series airplanes,
certificated in any category, serial numbers -004 through -063
inclusive.
Unsafe Condition
(d) This AD was prompted by disconnection of an electrical power
generator during an inspection flight, which was caused by a broken
terminal stud on the main relay. We are issuing this AD to prevent a
broken terminal stud on the main relay of an electrical power
generator, which could reduce the redundancy of electrical power
systems, result in increased pilot workload, and contribute to
reduced controllability of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection and Corrective Actions
(f) Within 6 months after the effective date of this AD, perform
a one-time general visual inspection to detect a broken terminal
stud on a main relay of the electrical power generator, and perform
corrective actions as applicable, by doing all of the actions in the
Accomplishment Instructions of Saab Service Bulletin 2000-24-017,
dated April 3, 2003. Although the service bulletin specifies to
submit certain information to the manufacturer, this AD does not
include that requirement.
Note 1: For the purposes of this AD, a general visual inspection
is: ``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
ensure visual access to all 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.''
[[Page 18277]]
Alternative Methods of Compliance (AMOCs)
(g) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
Related Information
(h) Swedish airworthiness directive 1-190, dated April 4, 2003,
also addresses the subject of this AD.
Material Incorporated by Reference
(i) You must use Saab Service Bulletin 2000-24-017, dated April
3, 2003, to perform the actions that are required by this AD, unless
the AD specifies otherwise. The Director of the Federal Register
approves the incorporation by reference of this document in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of
the service information, contact Saab Aircraft AB, SAAB Aircraft
Product Support, S-581.88, Link[ouml]ping, Sweden. To view the AD
docket, contact the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Room PL-401, Nassif
Building, Washington, DC. To review copies of the service
information, contact 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.
Issued in Renton, Washington, on March 31, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6915 Filed 4-8-05; 8:45 am]
BILLING CODE 4910-13-P
