Airworthiness Directives; Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B Airplanes, 19983-19986 [E8-7299]
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Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
Alternative Methods of Compliance
(AMOCs)
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 AD:
I
2008–08–08 Boeing: Amendment 39–15460.
Docket No. FAA–2008–0011; Directorate
Identifier 2007–NM–203–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective May 19, 2008.
Affected ADs
(b) None.
Unsafe Condition
(d) This AD results from a report that
several passenger masks with broken in-line
flow indicators were found following a mask
deployment. We are issuing this AD to
prevent the in-line flow indicators of the
passenger oxygen masks from fracturing and
separating, which could inhibit oxygen flow
to the masks and consequently result in
exposure of the passengers and cabin
attendants to hypoxia following a
depressurization event.
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.
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(g)(1) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
Material Incorporated by Reference
Applicability
(c) This AD applies to Boeing Model 757–
200, –200CB, –200PF, and –300 series
airplanes, certificated in any category; as
identified in Boeing Special Attention
Service Bulletin 757–35–0028, dated April 9,
2007.
Inspection and Corrective/Other Specified
Actions if Necessary
(f) Within 60 months after the effective
date of this AD, do a general visual
inspection to determine the manufacturer
and manufacture date of the oxygen masks in
the passenger service units and the lavatory
and attendant box assemblies, and do the
applicable corrective action, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 757–35–0028, dated April 9,
2007; except where the service bulletin
specifies repairing the oxygen mask
VerDate Aug<31>2005
assembly, replace it with a new or modified
oxygen mask assembly having an improved
flow indicator. The corrective action and
other specified action must be done before
further flight.
Note 1: The service bulletin refers to B/E
Aerospace Service Bulletin 174080–35–01,
dated February 6, 2006; and Revision 1,
dated May 1, 2006; as additional sources of
service information for modifying the oxygen
mask assembly by replacing the flow
indicator with an improved flow indicator.
15:37 Apr 11, 2008
Jkt 214001
(h) You must use Boeing Special Attention
Service Bulletin 757–35–0028, dated April 9,
2007, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
(3) You may review copies of the service
information incorporated by reference at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; 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.
Issued in Renton, Washington, on March
31, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–7297 Filed 4–11–08; 8:45 am]
BILLING CODE 4910–13–P
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19983
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29331; Directorate
Identifier 2007–NM–136–AD; Amendment
39–15459; AD 2008–08–07]
RIN 2120–AA64
Airworthiness Directives; Saab Model
SAAB–Fairchild SF340A (SAAB/
SF340A) and SAAB 340B Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This 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.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective May
19, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 19, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
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Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on September 28, 2007 (72 FR
55116). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
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.
Costs of Compliance
We estimate that this AD will affect
about 220 products of U.S. registry. We
also estimate that it will take about 9
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts cost would be negligible.
Where the service information lists
required parts costs that are covered
under warranty, we have assumed that
there will be no charge for these parts.
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 this AD to the U.S. operators to
be $158,400, or $720 per product.
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.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Clarification of Service Bulletin
Revisions
We have revised paragraph (f)(5) of
the final rule to clarify the applicable
service bulletin revisions for the parts
installation.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We determined that this change will not
increase the economic burden on any
operator or increase the scope of the AD.
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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
VerDate Aug<31>2005
15:37 Apr 11, 2008
Jkt 214001
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 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 this AD:
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
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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 and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
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 AD:
I
2008–08–07 Saab Aircraft AB: Amendment
39–15459. Docket No. FAA–2007–29331;
Directorate Identifier 2007–NM–136–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective May 19, 2008.
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.
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Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations
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
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 AIR83064–32–
12, dated January 2006; Revision 1, dated
January 23, 2006; and Revision 2, dated
March 30, 2006.
(iii) APPH Service Bulletin AIR83022–32–
32, dated January 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
AIR83064, or axle adaptor having P/N
AIR127308, AIR390226, or AIR130238,
unless it has been inspected and modified in
accordance with APPH Service Bulletin
AIR83022–32–32 or AIR83064–32–12, as
specified in paragraph (f)(3), (f)(4)(ii), or
(f)(4)(iii) of this AD, as applicable.
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.
FAA AD Differences
(i) You must use the service information
specified in Table 1 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Saab Aircraft AB, SAAB
Aircraft Product Support, S–581.88,
¨
Linkoping, Sweden.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; 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/cfr/ibrlocations.html.
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
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.
Material Incorporated by Reference
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Service Bulletin
Revision
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APPH Service Bulletin AIR83022–32–32 .......................................................................................................
APPH Service Bulletin AIR83064–32–12 .......................................................................................................
Saab Service Bulletin 340–32–133 .................................................................................................................
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Date
3
3
01
14APR1
April 26, 2006.
April 26, 2006.
May 3, 2006.
19986
Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations
Issued in Renton, Washington, on March
31, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–7299 Filed 4–11–08; 8:45 am]
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of May 19, 2008.
BILLING CODE 4910–13–P
For service information
identified in this AD, contact Boeing
Commercial Airplane Group, P.O. Box
3707, Seattle, Washington 98124–2207.
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
14 CFR Part 39
[Docket No. FAA–2007–29062; Directorate
Identifier 2007–NM–020–AD; Amendment
39–15462; AD 2008–08–10]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
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AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
For certain airplanes, this AD requires
replacing the outboard stabilizing fitting
and certain adjacent components of the
main landing gear (MLG) support beam.
This AD also requires repetitive
inspections for discrepancies of the
outboard stabilizing fitting, walking
beam hanger, and rear spar attachment,
and corrective actions if necessary. For
certain airplanes, this AD provides an
alternative one-time inspection of the
outboard stabilizing fitting for
discrepancies, and corrective actions if
necessary, which would extend the
compliance time for the replacement of
the outboard stabilizing fitting. For
certain other airplanes, this AD also
requires performing a torque check of
the aft pin of the outboard stabilizing
fitting, and corrective actions if
necessary. This AD results from reports
of findings of fatigue cracking of the
outboard stabilizing fitting and stress
corrosion cracking of the bolts attaching
the fitting to the wing rear spar. We are
issuing this AD to detect and correct
that cracking, which could result in
disconnection of the MLG actuator from
the rear spar and support beam,
consequent damage to the hydraulic
system, and possible loss of the ‘‘A’’ and
‘‘B’’ hydraulic systems and damage or
jamming of the flight control cables.
Damage or jamming of the flight control
cables could result in loss of control of
the airplane.
DATES: This AD is effective May 19,
2008.
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ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to all
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
That NPRM was published in the
Federal Register on August 31, 2007 (72
FR 50278). For certain airplanes, that
NPRM proposed to require replacing the
outboard stabilizing fitting and certain
adjacent components of the main
landing gear (MLG) support beam. That
NPRM also proposed to require
repetitive inspections for discrepancies
of the outboard stabilizing fitting,
walking beam hanger, and rear spar
attachment, and corrective actions if
necessary. For certain airplanes, that
NPRM proposed to provide an
alternative one-time inspection of the
outboard stabilizing fitting for
discrepancies and corrective actions if
necessary, which would extend the
compliance time for the replacement of
the outboard stabilizing fitting. For
certain other airplanes, that NPRM
proposed to require performing a torque
check of the aft pin of the outboard
stabilizing fitting, and corrective actions
if necessary.
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Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received from
the commenters.
Request To Change the Description of
the Unsafe Condition
Boeing asks that we change the
description of the unsafe condition
specified in the Summary and
Discussion sections and in paragraph (d)
of the AD. Boeing states that, Model
737–100, –200, –300, –400, and –500
airplanes are equipped with ‘‘A’’ and
‘‘B’’ hydraulic systems, and an
additional standby hydraulic system.
Boeing notes that fracture or disconnect
of any of the structural parts specified
in Boeing Alert Service Bulletin 737–
57A1266, Revision 1, dated January 3,
2007 (referenced in the NPRM as the
source of service information for
accomplishing the actions), could result
in damage to the ‘‘A’’ and ‘‘B’’ hydraulic
system tubes and damage or jamming of
the flight control cables. Boeing adds
that the standby hydraulic system is
protected from any damage from a
fracture or disconnect of any of the
structural parts because it is not in the
affected area. Additionally, Boeing
states that if the ‘‘A’’ and ‘‘B’’ hydraulic
systems fail, the standby system and
manual reversion enable control of the
airplane. Therefore, Boeing asks that the
description of the unsafe condition be
changed as follows: We are issuing this
AD to detect and correct that cracking,
which could result in disconnection of
the MLG actuator from the rear spar and
support beam, and consequent damage
to the hydraulic system, and possible
loss of the ‘‘A’’ and ‘‘B’’ hydraulic
systems and damage or jamming of the
flight control cables. Damage or
jamming of the flight control cables
could lead to a possible loss of control
of the airplane.
We agree with Boeing and have
changed the description of the unsafe
condition in the referenced sections as
follows: ‘‘We are issuing this AD to
detect and correct that cracking, which
could result in disconnection of the
MLG actuator from the rear spar and
support beam, consequent damage to
the hydraulic system, and possible loss
of the ‘‘A’’ and ‘‘B’’ hydraulic systems
and damage or jamming of the flight
control cables. Damage or jamming of
the flight control cables could result in
loss of control of the airplane.’’
However, the Discussion section is not
restated in the final rule; therefore, we
have made no change to the AD in this
regard.
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]]>Agencies
[Federal Register Volume 73, Number 72 (Monday, April 14, 2008)]
[Rules and Regulations]
[Pages 19983-19986]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-7299]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29331; Directorate Identifier 2007-NM-136-AD;
Amendment 39-15459; AD 2008-08-07]
RIN 2120-AA64
Airworthiness Directives; Saab Model SAAB-Fairchild SF340A (SAAB/
SF340A) and SAAB 340B Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This 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.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective May 19, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 19, 2008.
ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
[[Page 19984]]
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on September 28, 2007
(72 FR 55116). That NPRM proposed 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.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Clarification of Service Bulletin Revisions
We have revised paragraph (f)(5) of the final rule to clarify the
applicable service bulletin revisions for the parts installation.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the change described
previously. We determined that this change will not increase the
economic burden on any operator or increase the scope of the AD.
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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 220 products of U.S.
registry. We also estimate that it will take about 9 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Required parts cost would be
negligible. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these parts. 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 this AD to the
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 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 this AD:
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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.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 the NPRM, 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.
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 AD:
2008-08-07 Saab Aircraft AB: Amendment 39-15459. Docket No. FAA-
2007-29331; Directorate Identifier 2007-NM-136-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 19,
2008.
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.
[[Page 19985]]
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 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 AIR83064-32-12, dated January 2006;
Revision 1, dated January 23, 2006; and Revision 2, dated March 30,
2006.
(iii) APPH Service Bulletin AIR83022-32-32, dated January 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 AIR83064, or
axle adaptor having P/N AIR127308, AIR390226, or AIR130238, unless
it has been inspected and modified in accordance with APPH Service
Bulletin AIR83022-32-32 or AIR83064-32-12, as specified in paragraph
(f)(3), (f)(4)(ii), or (f)(4)(iii) of this AD, as applicable.
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.
Material Incorporated by Reference
(i) You must use the service information specified in Table 1 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Saab
Aircraft AB, SAAB Aircraft Product Support, S-581.88,
Link[ouml]ping, Sweden.
(3) You may review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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/cfr/ibr-
locations.html.
Table 1.--Material Incorporated by Reference
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Service Bulletin Revision Date
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APPH Service Bulletin 3 April 26, 2006.
AIR83022-32-32.
APPH Service Bulletin 3 April 26, 2006.
AIR83064-32-12.
Saab Service Bulletin 340-32- 01 May 3, 2006.
133.
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[[Page 19986]]
Issued in Renton, Washington, on March 31, 2008.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-7299 Filed 4-11-08; 8:45 am]
BILLING CODE 4910-13-P
