Airworthiness Directives; Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B Airplanes, 55116-55118 [E7-19202]
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55116
Federal Register / Vol. 72, No. 188 / Friday, September 28, 2007 / Proposed Rules
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2006–0219R1, dated June 29, 2007,
and the service information identified in
Table 1 of this AD, for related information.
TABLE 1.—SERVICE INFORMATION
Revision
level
Document
Time Limits Section of Part 1 of the ATR42–200/–300/–320 Maintenance Review Board Report ...........................
Time Limits Section of Part 1 of the ATR42–400/–500 Maintenance Review Board Report ....................................
Time Limits Section of Part 1 of the ATR72 Maintenance Review Board Report .....................................................
Issued in Renton, Washington, on
September 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–19201 Filed 9–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29331; Directorate
Identifier 2007–NM–136–AD]
RIN 2120–AA64
Airworthiness Directives; Saab Model
SAAB-Fairchild SF340A (SAAB/
SF340A) and SAAB 340B Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
pwalker on PROD1PC71 with PROPOSALS
A crack has been found in an axle adaptor
during fatigue testing. It was found that the
internal edges of the dowel holes did not
have the correct radius and the crack had
developed from the edge of one of the dowel
holes.
A crack in the axle adaptor can cause the
axle adaptor to fail and ultimately lead to
loss of the wheels and total loss of brake
capability.
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by October 29, 2007.
ADDRESSES: You may send comments by
any of the following methods:
VerDate Aug<31>2005
17:39 Sep 27, 2007
Jkt 211001
• DOT Docket Web Site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this proposed
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Mike Borfitz, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2677;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–29331; Directorate Identifier
2007–NM–136–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
PO 00000
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Fmt 4702
Sfmt 4702
7
6
8
Date
March 31, 2006.
March 26, 2007.
March 26, 2007.
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
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 we receive
about this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2006–0263,
dated August 29, 2006 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
A crack has been found in an axle adaptor
during fatigue testing. It was found that the
internal edges of the dowel holes did not
have the correct radius and the crack had
developed from the edge of one of the dowel
holes.
A crack in the axle adaptor can cause the
axle adaptor to fail and ultimately lead to
loss of the wheels and total loss of brake
capability.
The corrective action includes doing
repetitive ultrasonic inspections to
detect cracking in the axle adaptor;
replacing the axle adaptor if necessary;
and ultimately doing the terminating
action of inspecting and modifying the
main landing gear (MLG) shock strut
and axle adaptors. The inspection is a
crack test. The modification includes
measuring the dowel hole, and
corrective actions if necessary (replacing
the axle adaptor, repairing the dowel
hole) and, when accomplished,
terminates the repetitive inspection
requirements. You may obtain further
information by examining the MCAI in
the AD docket.
Relevant Service Information
Saab has issued Service Bulletin 340–
32–133, Revision 01, dated May 3, 2006.
APPH Limited has issued APPH Service
Bulletin AIR83064–32–12, Revision 3,
dated April 26, 2006; and AIR83022–
32–32, Revision 3, dated April 26, 2006.
E:\FR\FM\28SEP1.SGM
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Federal Register / Vol. 72, No. 188 / Friday, September 28, 2007 / Proposed Rules
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a NOTE within the
proposed AD.
pwalker on PROD1PC71 with PROPOSALS
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 220 products of U.S.
registry. We also estimate that it would
take about 9 work-hours per product to
comply with the basic requirements of
this proposed AD. Required parts cost
would be negligible. The average labor
rate is $80 per work-hour. Where the
service information lists required parts
costs that are covered under warranty,
we have assumed that there will be no
charge for these costs. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of the
proposed AD on U.S. operators to be
$158,400, or $720 per product.
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:
VerDate Aug<31>2005
17:39 Sep 27, 2007
Jkt 211001
55117
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.
Comments Due Date
(a) We must receive comments by October
29, 2007.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify 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. 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 proposed AD and placed it in the
AD docket.
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing Gear.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Saab Aircraft AB: Docket No. FAA–2007–
29331; Directorate Identifier 2007–NM–
136–AD.
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes listed
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category, unless equipped
with Main Landing Gear (MLG) shock struts
modified in accordance with APPH Service
Bulletin AIR83064–32–12 or AIR83022–32–
32.
(1) Saab Model SAAB-Fairchild SF340A
(SAAB/SF340A) airplanes, serial numbers (S/
Ns) SF340A–004 through –159.
(2) Saab Model SAAB 340B airplanes, S/Ns
340B–160 through –459.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
A crack has been found in an axle adaptor
during fatigue testing. It was found that the
internal edges of the dowel holes did not
have the correct radius and the crack had
developed from the edge of one of the dowel
holes.
A crack in the axle adaptor can cause the
axle adaptor to fail and ultimately lead to
loss of the wheels and total loss of brake
capability.
The corrective action includes doing
repetitive ultrasonic inspections to detect
cracking in the axle adaptor; replacing the
axle adaptor if necessary; and ultimately
doing the terminating action of inspecting
and modifying the main landing gear (MLG)
shock strut and axle adaptors. The inspection
is a crack test. The modification includes
measuring the dowel hole and corrective
actions if necessary (replacing the axle
adaptor, repairing the dowel hole), and,
when accomplished, terminates the repetitive
inspection requirements.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) Within 8,000 flight cycles since the last
MLG overhaul, or within 1,500 flight cycles,
or 6 months after the effective date of this
AD, whichever occurs latest: Inspect the
MLG in accordance with the
Accomplishment Instructions of Saab Service
Bulletin 340–32–133, Revision 01, dated May
3, 2006. If any crack is found, before further
flight: Replace the axle adaptor in accordance
with the Accomplishment Instructions of
Saab Service Bulletin 340–32–133, Revision
01, dated May 3, 2006.
(2) Repeat the inspection required by
paragraph (f)(1) of this AD thereafter at
intervals not to exceed 2,000 flight cycles
until the terminating action required by
paragraph (f)(3) of this AD is accomplished.
(3) Within 12,000 flight cycles after the
effective date of this AD, or at the next MLG
overhaul, whichever occurs earlier: Inspect
and modify the MLG shock strut and axle
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55118
Federal Register / Vol. 72, No. 188 / Friday, September 28, 2007 / Proposed Rules
adaptors in accordance with the
Accomplishment instructions of APPH
Service Bulletin AIR83064–32–12, Revision
3, dated April 26, 2006; or AIR83022–32–32,
Revision 3, dated April 26, 2006; as
applicable.
(4) Actions done before the effective date
of this AD in accordance with the service
bulletins listed in paragraphs (f)(4)(i),
(f)(4)(ii), and (f)(4)(iii) of this AD, as
applicable, are acceptable for compliance
with the corresponding actions in this AD.
(i) Saab Service Bulletin 340–32–133,
dated April 19, 2006.
(ii) APPH Service Bulletin AIR 83064–32–
12, dated January 18, 2006; Revision 1, dated
January 23, 2006; and Revision 2, dated
March 30, 2006.
(iii) APPH Service Bulletin AIR83022–32–
32, dated January 18, 2006; Revision 1, dated
January 23, 2006; and Revision 2, dated
March 30, 2006.
(5) As of the effective date of this AD, no
person may install an MLG shock strut
having part number (P/N) AIR83022 or
83064, or axle adaptor having P/N
AIR127308, 390226, or AIR130238, unless it
has been inspected and modified in
accordance with APPH Service Bulletin
AIR83022–32–32 or AIR83064–32–12.
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800, and
–900 Series Airplanes
FAA AD Differences
AGENCY:
pwalker on PROD1PC71 with PROPOSALS
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANM–116,
International Branch, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Mike Borfitz,
Aerospace Engineer, International Branch,
ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2677; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2006–0263, dated August 29, 2006;
VerDate Aug<31>2005
17:39 Sep 27, 2007
Jkt 211001
Saab Service Bulletin 340–32–133, Revision
01, dated May 3, 2006; APPH Service
Bulletin AIR83064–32–12, Revision 3, dated
April 26, 2006; and APPH Service Bulletin
AIR83022–32–32, Revision 3, dated April 26,
2006; for related information.
Issued in Renton, Washington, on
September 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–19202 Filed 9–27–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29333; Directorate
Identifier 2007–NM–141–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 737–600, –700,
–700C, –800, and –900 series airplanes.
This proposed AD would require
various repetitive inspections to detect
cracks along the chemically milled steps
of the fuselage skin or missing or loose
fasteners in the area of the preventative
modification or repairs, replacement of
the time-limited repair with the
permanent repair if applicable, and
applicable corrective actions if
necessary, which would end certain
repetitive inspections. This proposed
AD results from a fatigue test that
revealed numerous cracks in the upper
skin panel at the chemically milled step
above the lap joint. We are proposing
this AD to detect and correct such
fatigue-related cracks, which could
result in the crack tips continuing to
turn and grow to the point where the
skin bay flaps open, causing
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by November 13,
2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
• Governmentwide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6447; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2007–29333; Directorate
Identifier 2007–NM–141–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
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 proposed AD.
Using the search function of that 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 DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
E:\FR\FM\28SEP1.SGM
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]]>Agencies
[Federal Register Volume 72, Number 188 (Friday, September 28, 2007)]
[Proposed Rules]
[Pages 55116-55118]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-19202]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29331; Directorate Identifier 2007-NM-136-AD]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB-Fairchild SF340A (SAAB/
SF340A) and SAAB 340B Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
A crack has been found in an axle adaptor during fatigue
testing. It was found that the internal edges of the dowel holes did
not have the correct radius and the crack had developed from the
edge of one of the dowel holes.
A crack in the axle adaptor can cause the axle adaptor to fail
and ultimately lead to loss of the wheels and total loss of brake
capability.
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by October 29,
2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this proposed AD, the regulatory evaluation, any
comments received, and other information. The street address for the
Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Mike Borfitz, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2677; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
29331; Directorate Identifier 2007-NM-136-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
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 we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2006-0263, dated August 29, 2006 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
A crack has been found in an axle adaptor during fatigue
testing. It was found that the internal edges of the dowel holes did
not have the correct radius and the crack had developed from the
edge of one of the dowel holes.
A crack in the axle adaptor can cause the axle adaptor to fail
and ultimately lead to loss of the wheels and total loss of brake
capability.
The corrective action includes doing repetitive ultrasonic
inspections to detect cracking in the axle adaptor; replacing the axle
adaptor if necessary; and ultimately doing the terminating action of
inspecting and modifying the main landing gear (MLG) shock strut and
axle adaptors. The inspection is a crack test. The modification
includes measuring the dowel hole, and corrective actions if necessary
(replacing the axle adaptor, repairing the dowel hole) and, when
accomplished, terminates the repetitive inspection requirements. You
may obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
Saab has issued Service Bulletin 340-32-133, Revision 01, dated May
3, 2006. APPH Limited has issued APPH Service Bulletin AIR83064-32-12,
Revision 3, dated April 26, 2006; and AIR83022-32-32, Revision 3, dated
April 26, 2006.
[[Page 55117]]
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 220 products of U.S. registry. We also estimate that
it would take about 9 work-hours per product to comply with the basic
requirements of this proposed AD. Required parts cost would be
negligible. The average labor rate is $80 per work-hour. Where the
service information lists required parts costs that are covered under
warranty, we have assumed that there will be no charge for these costs.
As we do not control warranty coverage for affected parties, some
parties may incur costs higher than estimated here. Based on these
figures, we estimate the cost of the proposed AD on U.S. operators to
be $158,400, or $720 per product.
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify 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. 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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new AD:
Saab Aircraft AB: Docket No. FAA-2007-29331; Directorate Identifier
2007-NM-136-AD.
Comments Due Date
(a) We must receive comments by October 29, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes listed in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category, unless equipped
with Main Landing Gear (MLG) shock struts modified in accordance
with APPH Service Bulletin AIR83064-32-12 or AIR83022-32-32.
(1) Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) airplanes,
serial numbers (S/Ns) SF340A-004 through -159.
(2) Saab Model SAAB 340B airplanes, S/Ns 340B-160 through -459.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
A crack has been found in an axle adaptor during fatigue
testing. It was found that the internal edges of the dowel holes did
not have the correct radius and the crack had developed from the
edge of one of the dowel holes.
A crack in the axle adaptor can cause the axle adaptor to fail
and ultimately lead to loss of the wheels and total loss of brake
capability.
The corrective action includes doing repetitive ultrasonic
inspections to detect cracking in the axle adaptor; replacing the
axle adaptor if necessary; and ultimately doing the terminating
action of inspecting and modifying the main landing gear (MLG) shock
strut and axle adaptors. The inspection is a crack test. The
modification includes measuring the dowel hole and corrective
actions if necessary (replacing the axle adaptor, repairing the
dowel hole), and, when accomplished, terminates the repetitive
inspection requirements.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 8,000 flight cycles since the last MLG overhaul, or
within 1,500 flight cycles, or 6 months after the effective date of
this AD, whichever occurs latest: Inspect the MLG in accordance with
the Accomplishment Instructions of Saab Service Bulletin 340-32-133,
Revision 01, dated May 3, 2006. If any crack is found, before
further flight: Replace the axle adaptor in accordance with the
Accomplishment Instructions of Saab Service Bulletin 340-32-133,
Revision 01, dated May 3, 2006.
(2) Repeat the inspection required by paragraph (f)(1) of this
AD thereafter at intervals not to exceed 2,000 flight cycles until
the terminating action required by paragraph (f)(3) of this AD is
accomplished.
(3) Within 12,000 flight cycles after the effective date of this
AD, or at the next MLG overhaul, whichever occurs earlier: Inspect
and modify the MLG shock strut and axle
[[Page 55118]]
adaptors in accordance with the Accomplishment instructions of APPH
Service Bulletin AIR83064-32-12, Revision 3, dated April 26, 2006;
or AIR83022-32-32, Revision 3, dated April 26, 2006; as applicable.
(4) Actions done before the effective date of this AD in
accordance with the service bulletins listed in paragraphs
(f)(4)(i), (f)(4)(ii), and (f)(4)(iii) of this AD, as applicable,
are acceptable for compliance with the corresponding actions in this
AD.
(i) Saab Service Bulletin 340-32-133, dated April 19, 2006.
(ii) APPH Service Bulletin AIR 83064-32-12, dated January 18,
2006; Revision 1, dated January 23, 2006; and Revision 2, dated
March 30, 2006.
(iii) APPH Service Bulletin AIR83022-32-32, dated January 18,
2006; Revision 1, dated January 23, 2006; and Revision 2, dated
March 30, 2006.
(5) As of the effective date of this AD, no person may install
an MLG shock strut having part number (P/N) AIR83022 or 83064, or
axle adaptor having P/N AIR127308, 390226, or AIR130238, unless it
has been inspected and modified in accordance with APPH Service
Bulletin AIR83022-32-32 or AIR83064-32-12.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Mike
Borfitz, Aerospace Engineer, International Branch, ANM-116, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-2677; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2006-0263, dated
August 29, 2006; Saab Service Bulletin 340-32-133, Revision 01,
dated May 3, 2006; APPH Service Bulletin AIR83064-32-12, Revision 3,
dated April 26, 2006; and APPH Service Bulletin AIR83022-32-32,
Revision 3, dated April 26, 2006; for related information.
Issued in Renton, Washington, on September 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-19202 Filed 9-27-07; 8:45 am]
BILLING CODE 4910-13-P
