Airworthiness Directives; BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes, 48290-48292 [E8-18810]
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48290
Federal Register / Vol. 73, No. 161 / Tuesday, August 19, 2008 / Rules and Regulations
TABLE 1—APPLICABILITY
Boeing model—
As identified in Boeing Alert Service Bulletin—
737–100, –200, and –200C series airplanes ...........................................
737–300, –400, and –500 series airplanes ..............................................
737–53A1197, dated August 25, 2006.
737–53A1188, Revision 2, dated May 9, 2007, or 737–53A1197, dated
August 25, 2006.
Unsafe Condition
(d) This AD results from reports of cracks
found at the cutout in the web of body station
frame 303.9 inboard of stringer 16L. We are
issuing this AD to detect and correct such
cracking, which could prevent the left
forward entry door from sealing correctly,
and could cause in-flight decompression 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.
ebenthall on PRODPC60 with RULES
Repetitive Inspections: Service Bulletin 737–
53A1188
(f) For airplanes identified in Boeing Alert
Service Bulletin 737–53A1188, Revision 2,
dated May 9, 2007, including airplanes
modified by the repair/preventive change
specified in the original version, dated April
9, 1998; or Revision 1, dated March 18, 1999;
of the service bulletin: Do detailed and high
frequency eddy current (HFEC) inspections
in the web and doubler around the slotted
holes in the frame web at stringers 15L and
16L, in accordance with the Accomplishment
Instructions of Revision 2 of the service
bulletin. Do the inspections at the applicable
time specified in paragraph 1.E. of Revision
2 of the service bulletin, except as provided
by paragraph (h) of this AD. Do all applicable
corrective actions before further flight in
accordance with Revision 2 of the service
bulletin, except as provided by paragraph (i)
of this AD. Repeat the inspections at intervals
not to exceed 4,500 flight cycles until
accomplishment of the repair/preventive
change in accordance with Revision 2 of the
service bulletin, which terminates the
repetitive inspection requirements. A repair/
preventive change done in accordance with
the original version or Revision 1 of the
service bulletin does not terminate the
repetitive inspections, but the repetitive
inspections may be terminated after the
existing kit is replaced with a new kit in
accordance with paragraph 3.B., Part II, step
3, or Part III, step 3, of Revision 2 of the
service bulletin.
Repetitive Inspections: Service Bulletin 737–
53A1197
(g) For airplanes identified in Boeing Alert
Service Bulletin 737–53A1197, dated August
25, 2006: Do an ultrasound inspection of the
slot-shaped cutout in the web for the door
stop strap at stringer 16L, an HFEC
inspection of the web along the upper and
lower edges of the doubler around the
doorstop strap at stringer 16L, and a detailed
inspection of the web around the doubler for
the cutout at stringer 16L, in accordance with
the Accomplishment Instructions of the
VerDate Aug<31>2005
15:10 Aug 18, 2008
Jkt 214001
service bulletin. Do the inspections at the
applicable time specified in paragraph 1.E. of
the service bulletin, except as provided by
paragraph (h) of this AD. Do all applicable
corrective actions before further flight in
accordance with the service bulletin, except
as provided by paragraph (i) of this AD.
Repeat the inspections at intervals not to
exceed 4,500 flight cycles, until
accomplishment of the repair/preventive
change in accordance with the service
bulletin, which terminates the repetitive
inspections.
Exceptions to Service Bulletin Specifications
(h) Where Boeing Alert Service Bulletin
737–53A1188, Revision 2, dated May 9, 2007,
and Boeing Alert Service Bulletin 737–
53A1197, dated August 25, 2006, specify a
compliance time after release of the service
bulletin, this AD requires compliance within
the specified time after the effective date of
this AD. For the initial inspection, the grace
period for airplanes that have exceeded the
specified threshold is extended to 4,500
flight cycles after the effective date of this
AD.
(i) Where Boeing Alert Service Bulletin
737–53A1188, Revision 2, dated May 9, 2007,
and Boeing Alert Service Bulletin 737–
53A1197, dated August 25, 2006, specify to
contact Boeing for appropriate action,
including repair of damage outside the scope
of the service bulletin, repair using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle Aircraft
Certification Office, FAA, ATTN: Howard
Hall, Aerospace Engineer, Airframe Branch,
ANM–120S; telephone (425) 917–6430; fax
(425) 917–6590; has the authority to approve
AMOCs for this AD, if requested using 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
Material Incorporated by Reference
(k) You must use Boeing Alert Service
Bulletin 737–53A1188, Revision 2, dated
May 9, 2007; or Boeing Alert Service Bulletin
737–53A1197, dated August 25, 2006; as
applicable; 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 August
6, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–18812 Filed 8–18–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0622; Directorate
Identifier 2008–NM–064–AD; Amendment
39–15642; AD 2008–17–04]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited
(Jetstream) Model 4101 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
E:\FR\FM\19AUR1.SGM
19AUR1
Federal Register / Vol. 73, No. 161 / Tuesday, August 19, 2008 / Rules and Regulations
product. The MCAI describes the unsafe
condition as:
Resulting from the assessment of fuel tank
wiring installations required by SFAR 88
(Special Federal Aviation Regulation 88) and
equivalent JAA/EASA (Joint Aviation
Authorities/European Aviation Safety
Agency) policy, BAE Systems identified
* * * features in the Jetstream 4100 where
the need for design changes was apparent.
* * *
Internal fuel tank wiring chafing damage,
if not corrected, could lead to ignition of fuel
vapours and subsequent fuel tank explosion.
*
*
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
September 23, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 23, 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:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1175; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
ebenthall on PRODPC60 with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 9, 2008 (73 FR 32488).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Resulting from the assessment of fuel tank
wiring installations required by SFAR 88
(Special Federal Aviation Regulation 88) and
equivalent JAA/EASA (Joint Aviation
Authorities/European Aviation Safety
Agency) policy, BAE Systems identified two
features in the Jetstream 4100 where the need
for design changes was apparent. One of
these is addressed by Service Bulletin (SB)
J41–28–014 which introduces changes to the
wiring harness installations to the left (LH)
and right (RH) fuel boost pumps, identified
by modification number JM41672. In
addition, to detect excessive cable lengths
and evidence of chafing damage, SB J41–28–
014 provides instructions to inspect and
correct, as necessary, the internal fuel tank
wiring routed to the LH and RH high level
sensors.
VerDate Aug<31>2005
15:10 Aug 18, 2008
Jkt 214001
Internal fuel tank wiring chafing damage,
if not corrected, could lead to ignition of fuel
vapours and subsequent fuel tank explosion.
For the reason stated above, this EASA
Airworthiness Directive (AD) requires the
replacement of the (LH and RH) fuel boost
pump metallic conduit assemblies with loom
assemblies and the inspection of internal fuel
tank high level sensor wiring, including
corrective actions, as necessary.
Corrective actions include replacing
any damaged internal fuel tank high
level sensor wiring and removing excess
wiring. 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.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
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 7
products of U.S. registry. We also
estimate that it will take 47 work-hours
per product to comply with the basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Required parts will cost about $7,000
per product. 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
$75,320, or $10,760 per product.
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
48291
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.
E:\FR\FM\19AUR1.SGM
19AUR1
48292
Federal Register / Vol. 73, No. 161 / Tuesday, August 19, 2008 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
tank high level sensor wiring, including
corrective actions, as necessary.
Corrective actions include replacing any
damaged internal fuel tank high level sensor
wiring and removing excess wiring.
Adoption of the Amendment
Actions and Compliance
(f) Unless already done: Within 24 months
after the effective date of this AD, do the
following actions.
(1) Modify the LH and RH wing fuel boost
pump wiring in accordance with paragraphs
2.B. and 2.C. of the Accomplishment
Instructions of BAE Systems (Operations)
Limited Service Bulletin J41–28–014,
Revision 1, dated December 21, 2007.
(2) Inspect the LH and RH wing fuel high
level sensor wiring in accordance with
paragraph 2.D. of the Accomplishment
Instructions of BAE Systems (Operations)
Limited Service Bulletin J41–28–014,
Revision 1, dated December 21, 2007.
(3) When excess wiring and/or damaged
wiring is found during the inspection
required by paragraph (f)(2) of this AD, before
next flight, accomplish the corrective actions
as specified in paragraph 2.D. of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Service
Bulletin J41–28–014, Revision 1, dated
December 21, 2007.
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
2008–17–04 BAE Systems (Operations)
Limited (Formerly British Aerospace
Regional Aircraft): Amendment 39–
15642. Docket No. FAA–2008–0622;
Directorate Identifier 2008–NM–064–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 23, 2008.
FAA AD Differences
Affected ADs
(b) None.
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model Jetstream 4101
airplanes, certificated in any category, all
serial numbers.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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: Todd Thompson,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1175; 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.
ebenthall on PRODPC60 with RULES
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Resulting from the assessment of fuel tank
wiring installations required by SFAR 88
(Special Federal Aviation Regulation 88) and
equivalent JAA/EASA (Joint Aviation
Authorities/European Aviation Safety
Agency) policy, BAE Systems identified two
features in the Jetstream 4100 where the need
for design changes was apparent. One of
these is addressed by Service Bulletin (SB)
J41–28–014 which introduces changes to the
wiring harness installations to the left (LH)
and right (RH) fuel boost pumps, identified
by modification number JM41672. In
addition, to detect excessive cable lengths
and evidence of chafing damage, SB J41–28–
014 provides instructions to inspect and
correct, as necessary, the internal fuel tank
wiring routed to the LH and RH high level
sensors.
Internal fuel tank wiring chafing damage,
if not corrected, could lead to ignition of fuel
vapours and subsequent fuel tank explosion.
For the reason stated above, this EASA
Airworthiness Directive (AD) requires the
replacement of the (LH and RH) fuel boost
pump metallic conduit assemblies with loom
assemblies and the inspection of internal fuel
VerDate Aug<31>2005
15:10 Aug 18, 2008
Jkt 214001
2008; and BAE Systems (Operations) Limited
Service Bulletin J41–28–014, Revision 1,
dated December 21, 2007; for related
information.
Material Incorporated by Reference
(i) You must use BAE Systems (Operations)
Limited Service Bulletin J41–28–014,
Revision 1, dated December 21, 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 British Aerospace Regional
Aircraft American Support, 13850 Mclearen
Road, Herndon, Virginia 20171.
(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.
Issued in Renton, Washington, on August
5, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–18810 Filed 8–18–08; 8:45 am]
BILLING CODE 4910–13–P
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2008–0041, dated February 27,
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0649; Directorate
Identifier 2008–CE–038–AD; Amendment
39–15646; AD 2008–17–08]
RIN 2120–AA64
Airworthiness Directives; DG
Flugzeugbau GmbH Model DG–500MB
Powered Sailplanes
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)
issued 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 DG–500MB experienced, after the engine
shutdown, an uncommanded retraction of its
powerplant.
Investigations revealed that some bolts of
the extension retraction mechanism had
E:\FR\FM\19AUR1.SGM
19AUR1
]]>Agencies
[Federal Register Volume 73, Number 161 (Tuesday, August 19, 2008)]
[Rules and Regulations]
[Pages 48290-48292]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-18810]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0622; Directorate Identifier 2008-NM-064-AD;
Amendment 39-15642; AD 2008-17-04]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited
(Jetstream) Model 4101 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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
[[Page 48291]]
product. The MCAI describes the unsafe condition as:
Resulting from the assessment of fuel tank wiring installations
required by SFAR 88 (Special Federal Aviation Regulation 88) and
equivalent JAA/EASA (Joint Aviation Authorities/European Aviation
Safety Agency) policy, BAE Systems identified * * * features in the
Jetstream 4100 where the need for design changes was apparent. * * *
Internal fuel tank wiring chafing damage, if not corrected,
could lead to ignition of fuel vapours and subsequent fuel tank
explosion.
* * * * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective September 23, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
23, 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: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on June 9, 2008 (73 FR
32488). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Resulting from the assessment of fuel tank wiring installations
required by SFAR 88 (Special Federal Aviation Regulation 88) and
equivalent JAA/EASA (Joint Aviation Authorities/European Aviation
Safety Agency) policy, BAE Systems identified two features in the
Jetstream 4100 where the need for design changes was apparent. One
of these is addressed by Service Bulletin (SB) J41-28-014 which
introduces changes to the wiring harness installations to the left
(LH) and right (RH) fuel boost pumps, identified by modification
number JM41672. In addition, to detect excessive cable lengths and
evidence of chafing damage, SB J41-28-014 provides instructions to
inspect and correct, as necessary, the internal fuel tank wiring
routed to the LH and RH high level sensors.
Internal fuel tank wiring chafing damage, if not corrected,
could lead to ignition of fuel vapours and subsequent fuel tank
explosion.
For the reason stated above, this EASA Airworthiness Directive
(AD) requires the replacement of the (LH and RH) fuel boost pump
metallic conduit assemblies with loom assemblies and the inspection
of internal fuel tank high level sensor wiring, including corrective
actions, as necessary.
Corrective actions include replacing any damaged internal fuel tank
high level sensor wiring and removing excess wiring. 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.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
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 7 products of U.S. registry.
We also estimate that it will take 47 work-hours per product to comply
with the basic requirements of this AD. The average labor rate is $80
per work-hour. Required parts will cost about $7,000 per product. 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
$75,320, or $10,760 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.
[[Page 48292]]
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:
2008-17-04 BAE Systems (Operations) Limited (Formerly British
Aerospace Regional Aircraft): Amendment 39-15642. Docket No. FAA-
2008-0622; Directorate Identifier 2008-NM-064-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 23, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model Jetstream 4101 airplanes, certificated in any category, all
serial numbers.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Resulting from the assessment of fuel tank wiring installations
required by SFAR 88 (Special Federal Aviation Regulation 88) and
equivalent JAA/EASA (Joint Aviation Authorities/European Aviation
Safety Agency) policy, BAE Systems identified two features in the
Jetstream 4100 where the need for design changes was apparent. One
of these is addressed by Service Bulletin (SB) J41-28-014 which
introduces changes to the wiring harness installations to the left
(LH) and right (RH) fuel boost pumps, identified by modification
number JM41672. In addition, to detect excessive cable lengths and
evidence of chafing damage, SB J41-28-014 provides instructions to
inspect and correct, as necessary, the internal fuel tank wiring
routed to the LH and RH high level sensors.
Internal fuel tank wiring chafing damage, if not corrected,
could lead to ignition of fuel vapours and subsequent fuel tank
explosion.
For the reason stated above, this EASA Airworthiness Directive
(AD) requires the replacement of the (LH and RH) fuel boost pump
metallic conduit assemblies with loom assemblies and the inspection
of internal fuel tank high level sensor wiring, including corrective
actions, as necessary.
Corrective actions include replacing any damaged internal fuel
tank high level sensor wiring and removing excess wiring.
Actions and Compliance
(f) Unless already done: Within 24 months after the effective
date of this AD, do the following actions.
(1) Modify the LH and RH wing fuel boost pump wiring in
accordance with paragraphs 2.B. and 2.C. of the Accomplishment
Instructions of BAE Systems (Operations) Limited Service Bulletin
J41-28-014, Revision 1, dated December 21, 2007.
(2) Inspect the LH and RH wing fuel high level sensor wiring in
accordance with paragraph 2.D. of the Accomplishment Instructions of
BAE Systems (Operations) Limited Service Bulletin J41-28-014,
Revision 1, dated December 21, 2007.
(3) When excess wiring and/or damaged wiring is found during the
inspection required by paragraph (f)(2) of this AD, before next
flight, accomplish the corrective actions as specified in paragraph
2.D. of the Accomplishment Instructions of BAE Systems (Operations)
Limited Service Bulletin J41-28-014, Revision 1, dated December 21,
2007.
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,
International Branch, ANM-116, 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: Todd
Thompson, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1175; 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 2008-0041, dated
February 27, 2008; and BAE Systems (Operations) Limited Service
Bulletin J41-28-014, Revision 1, dated December 21, 2007; for
related information.
Material Incorporated by Reference
(i) You must use BAE Systems (Operations) Limited Service
Bulletin J41-28-014, Revision 1, dated December 21, 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
British Aerospace Regional Aircraft American Support, 13850 Mclearen
Road, Herndon, Virginia 20171.
(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.
Issued in Renton, Washington, on August 5, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-18810 Filed 8-18-08; 8:45 am]
BILLING CODE 4910-13-P
