Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and -300A Series Airplanes, 13106-13109 [E8-4673]
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Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
TABLE 3.—ALL MATERIAL INCORPORATED BY REFERENCE
Service information
Airbus
Airbus
Airbus
Airbus
Airbus
Airbus
Service
Service
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
A330–27–3134 ...........................................................................................................
A330–27–3136 ...........................................................................................................
A330–27–3138, excluding Appendix 01 ....................................................................
A340–27–4132 ...........................................................................................................
A340–27–4135 ...........................................................................................................
A340–27–4137, excluding Appendix 01 ....................................................................
(2) On November 29, 2005 (70 FR 69065,
November 14, 2005), the Director of the
Federal Register approved the incorporation
by reference of Airbus All Operators Telex
A330–27A3138, Revision 01, dated October
3, 2005; and Airbus All Operators Telex
A340–27A4137, Revision 01, dated October
3, 2005.
(3) For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France. 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 March 3,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–4671 Filed 3–11–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; BAE
Systems (Operations) Limited Model
BAe 146–100A, –200A, and –300A
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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:
SUMMARY:
jlentini on PROD1PC65 with RULES
This condition could result in reduced
structural integrity of the airplane. We
are issuing this AD to require actions to
correct the unsafe condition on these
products.
This AD becomes effective April
16, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 16, 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, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–1175;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
DATES:
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 December 20, 2007 (72 FR
72270). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
RIN 2120–AA64
17:40 Mar 11, 2008
Cracking has been found on the centre
fuselage top aft longeron at Rib ‘0’ on an inservice aircraft. * * *
Discussion
[Docket No. FAA–2007–0368; Directorate
Identifier 2007–NM–050–AD; Amendment
39–15420; AD 2008–06–08]
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Revision
Jkt 214001
Cracking has been found on the centre
fuselage top aft longeron at Rib ‘0’ on an inservice aircraft. Subsequent investigation has
indicated that the currently defined
threshold and repeat inspection period must
be reduced, and the area of inspection
expanded for the BAe 146 series 100 and 200.
For the BAe146 series 300, only the repeat
inspection period must be reduced, and the
area of inspection expanded.
Cracking on the center fuselage top aft
longeron at Rib ‘0,’ could result in
reduced structural integrity of the
airplane. Corrective actions include
repetitive inspections of the center
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01 ................
01 ................
02 ................
Original ........
Original ........
02 ................
Date
May 12, 2006.
July 19, 2006.
May 30, 2006.
October 13, 2005.
January 12, 2006.
May 30, 2006.
fuselage top aft longeron for cracking
and repair/replacement if necessary.
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.
Revision to the Reference to the
Nondestructive Testing (NDT) Manual
We have removed the reference to the
BAE Systems (Operations) Limited BAe
146/Avro 146–RJ Series NDT Manual
Part 6 20–00–03 from paragraphs
(f)(2)(iii) and (f)(5)(iii) of this AD. The
appropriate source of service
information for doing the inspection
and repair specified in paragraphs
(f)(2)(iii) and (f)(5)(iii) of this AD is BAE
Systems (Operations) Limited
Inspection Service Bulletin ISB.53–173,
Revision 2, dated March 28, 2006. The
Accomplishment Instructions of the
service bulletin refer to the NDT
manual. We have added Note 1 and
Note 3 to this AD to clarify that the
service bulletin refers to the NDT
manual as a secondary source of service
information for doing the inspection.
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 these changes 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.
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Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
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 1 product of U.S. registry. We also
estimate that it will take about 8 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $640, or $640 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.
jlentini on PROD1PC65 with RULES
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.
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17:40 Mar 11, 2008
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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
2008–06–08 BAE Systems (Operations)
Limited (Formerly British Aerospace
Regional Aircraft): Amendment 39–
15420. Docket No. FAA–2007–0368;
Directorate Identifier 2007–NM–050–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective April 16, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model BAe 146–100A,
–200A, and –300A series airplanes;
certificated in any category.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Cracking has been found on the centre
fuselage top aft longeron at Rib ‘0’ on an inservice aircraft. Subsequent investigation has
indicated that the currently defined
threshold and repeat inspection period must
be reduced, and the area of inspection
expanded for the BAe 146 series 100 and 200.
For the BAe 146 series 300, only the repeat
inspection period must be reduced, and the
area of inspection expanded.
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Cracking on the center fuselage top aft
longeron at Rib ‘0’ could result in reduced
structural integrity of the airplane. Corrective
actions include repetitive inspections of the
center fuselage top aft longeron for cracking
and repair/replacement if necessary.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) For all Model BAe 146–100A and BAE
146–200A series airplanes pre-mod
HCM01709B or HCM01709C that have not
been inspected in accordance with BAE
Systems (Operations) Limited BAe 146
Maintenance Review Board Report (MRBR)
SSI/SII Task No. 53–20–140A (Maintenance
Planning Document (MPD) Task 532040–
SDI–10000–3) or BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
173, Revision 1, dated May 19, 2004, as of
the effective date of this AD: Do the actions
in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD
at the applicable compliance time, and do all
applicable repairs and replacements before
further flight.
(i) Inspect and repair cracking of the
forward six bolt bores between the subframe
and frame 30 in accordance with paragraph
2.B of the Accomplishment Instructions of
BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53–173,
Revision 2, dated March 28, 2006, before the
accumulation of 17,000 total flight cycles, or
within 500 flight cycles after the effective
date of this AD, whichever occurs later. If the
damage exceeds limits specified in the
structural repair manual (SRM), before
further flight, contact BAE Systems and
repair. Repeat the inspection thereafter at
intervals not to exceed 5,000 flight cycles,
except as provided by paragraph (f)(3) of this
AD.
(ii) Inspect and repair cracking of the
remaining fastener bores between the subframe and frame 30 in accordance with
paragraph 2.B of the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
173, Revision 2, dated March 28, 2006, before
the accumulation of 17,000 total flight cycles,
or within 4,000 flight cycles after the
effective date of this AD, whichever occurs
later. If the damage exceeds limits specified
in the SRM, before further flight, contact BAE
Systems and repair. Repeat the inspection
thereafter at intervals not to exceed 11,900
flight cycles, except as provided by
paragraph (f)(3) of this AD.
(2) For all Model BAe 146–100A and BAe
146–200A series airplanes pre-mod
HCM01709B or HCM01709C that have been
inspected in accordance with BAE Systems
(Operations) Limited BAe 146 MRBR SSI/SII
Task No. 53–20–140A (MPD task 532040–
SDI–10000–3) or BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
173 Revision 1, May 19, 2004, as of the
effective date of this AD: Do the actions in
paragraphs (f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of
this AD at the applicable compliance time,
and do all applicable repairs and
replacements before further flight.
(i) Do an ultrasonic inspection and repair
cracking of the forward six bolt bores
between the subframe and frame 30 in
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Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
accordance with paragraph 2.B of the
Accomplishment Instructions and Appendix
2 of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53–173,
Revision 2, dated March 28, 2006, before the
accumulation of 5,400 flight cycles since last
inspection, or within 500 flight cycles after
the effective date of this AD, whichever
occurs later. If the damage exceeds limits
specified in the SRM, before further flight,
contact BAE Systems and repair. Repeat the
inspection thereafter at intervals not to
exceed 5,000 flight cycles, except as provided
by paragraph (f)(3) of this AD.
(ii) Do a high frequency eddy current
inspection and repair cracking of the forward
six bolt bores between the subframe and
frame 30 in accordance with paragraph 2.B
of the Accomplishment Instructions and
Appendix 3 of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
173, Revision 2, dated March 28, 2006,
within 4,000 flight cycles after the effective
date of this AD. If the damage exceeds limits
specified in the SRM, before further flight,
contact BAE systems and repair. Repeat the
inspection thereafter at intervals not to
exceed 5,000 flight cycles, except as provided
by paragraph (f)(3) of this AD.
(iii) Do a rotating eddy current inspection
and repair cracking of the remaining fastener
bores between the sub-frame and frame 30 in
accordance with paragraph 2.B of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–173, Revision 2,
dated March 28, 2006, within 4,000 flight
cycles after the effective date of this AD. If
the damage exceeds limits specified in the
SRM, before further flight, contact BAE
Systems and repair. Repeat the inspection
thereafter at intervals not to exceed 11,900
flight cycles, except as provided by
paragraph (f)(3) of this AD.
Note 1: BAE Systems (Operations) Limited
Inspection Service Inspection Bulletin
ISB.53–173, Revision 2, dated March 28,
2006, refers to the BAE Systems (Operations)
Limited BAe 146/Avro 146–RJ Series
Nondestructive Testing (NDT) Manual Part 6
20–00–03 as a secondary source of service
information for doing the eddy current
inspection.
(3) For all Model BAe 146–100A and BAe
146–200A series airplanes pre-mod
HCM01709B or HCM01709C that have had a
replacement aft longeron installed: Prior to
the accumulation of 17,000 flight cycles after
the aft longeron replacement, or within 500
flight cycles after the effective date of this
AD, whichever occurs later, inspect for
cracking of the forward six bolt bores and the
fastener bores between the sub-frame and
frame 30, and repair any crack before further
flight in accordance with paragraph 2.B of
the Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–173, Revision 2,
dated March 28, 2006. If the damage exceeds
limits specified in the SRM, before further
flight, contact BAE Systems and repair.
Repeat the inspection thereafter at intervals
not to exceed 5,000 flight cycles for the
forward six bolt bores, and 11,900 flight
cycles for the remaining fastener bores
between the sub-frame and frame 30.
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Replacing the longeron terminates the
repetitive inspection requirements of
paragraph (f)(1) and (f)(2) of this AD; postreplacement inspections must be done in
accordance with this paragraph.
Note 2: The threshold for an aircraft is reset
if a replacement longeron is fitted.
(4) For all Model BAe 146–300A series
airplanes pre-mod HCM01709A that have not
been inspected in accordance with BAE
Systems (Operations) Limited BAe 146
MRBR SSI/SII Task No. 53–20–140A (MPD
Task 532040–SDI–10000–3) or BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.53–173, Revision 1, dated May
19, 2004, as of the effective date of this AD:
Do the actions in paragraphs (f)(4)(i) and
(f)(4)(ii) of this AD at the applicable
compliance time, and do all applicable
repairs and replacements before further
flight.
(i) Inspect and repair cracking of the
forward six bolt bores between the subframe
and frame 30 in accordance with paragraph
2.B of the Accomplishment Instructions of
BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53–173,
Revision 2, dated March 28, 2006, prior to
the accumulation of 24,000 total flight cycles,
or within 500 flight cycles after the effective
date of this AD, whichever occurs later. If the
damage exceeds limits specified in the SRM,
before further flight, contact BAE Systems
and repair. Repeat the inspection thereafter at
intervals not to exceed 4,000 flight cycles,
except as provided by paragraph (f)(6) of this
AD.
(ii) Inspect and repair cracking of the
remaining fastener bores between the subframe and frame 30 in accordance with
paragraph 2.B of the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
173, Revision 2, dated March 28, 2006, at the
later of 24,000 total flight cycles, or within
4,000 flight cycles after the effective date of
this AD. If the damage exceeds limits
specified in the SRM, before further flight,
contact BAE Systems and repair. Repeat the
inspection thereafter at intervals not to
exceed 11,900 flight cycles, except as
provided by paragraph (f)(6) of this AD.
(5) For all Model BAe 146–300A series
airplanes pre-mod HCM01709A that have
been inspected in accordance with BAE
Systems (Operations) Limited BAe 146
MRBR SSI/SII Task No. 53–20–140A (MPD
task 532040–SDI–10000–3) or BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.53–173, Revision 1, May 19,
2004, as of the effective date of this AD: Do
the actions in paragraphs (f)(5)(i), (f)(5)(ii),
and (f)(5)(iii) of this AD at the applicable
compliance time, and do all applicable
repairs and replacements before further
flight.
(i) Do an ultrasonic inspection and repair
cracking of the forward six bores between the
subframe and frame 30 in accordance with
paragraph 2.B of the Accomplishment
Instructions and Appendix 2 of BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.53–173, Revision 2, dated March
28, 2006, within 4,000 flight cycles since last
inspection, or within 500 flight cycles after
the effective date of this AD, whichever
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occurs later. If the damage exceeds limits
specified in the SRM, before further flight,
contact BAE Systems and repair. Repeat the
inspection thereafter at intervals not to
exceed 4,000 flight cycles except as provided
by paragraph (f)(6) of this AD.
(ii) Do a high frequency eddy current
inspection and repair cracking of the forward
six bolt bores between the subframe and
frame 30 in accordance with paragraph 2.B
of the Accomplishment Instructions and
Appendix 3 of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
173, Revision 2, dated March 28, 2006,
within 4,000 flight cycles after the effective
date of this AD. If the damage exceeds limits
specified in the SRM, before further flight,
contact BAE Systems and repair. Repeat the
inspection thereafter at intervals not to
exceed 4,000 flight cycles, except as provided
by paragraph (f)(6) of this AD.
(iii) Do a rotating eddy current inspection
and repair cracking of the remaining fastener
bores between the sub-frame and frame 30 in
accordance with paragraph 2.B of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–173, Revision 2,
dated March 28, 2006, within 4,000 flight
cycles after the effective date of this AD. If
the damage exceeds limits specified in the
SRM, before further flight, contact BAE
Systems and repair. Repeat the inspection
thereafter at intervals not to exceed 11,900
flight cycles, except as provided by
paragraph (f)(6) of this AD.
Note 3: BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53–173,
Revision 2, dated March 28, 2006, refers to
the BAE Systems (Operations) Limited BAe
146/Avro 146–RJ Series NDT Manual Part 6
20–00–03 as a secondary source of service
information for doing the eddy current
inspection.
(6) For all Model BAe 146–300A series
airplanes pre-mod HCM01709A that have
had a replacement aft longeron installed:
Prior to the accumulation of 24,000 flight
cycles after the aft longeron replacement, or
within 500 flight cycles after the effective
date of this AD, whichever occurs later,
inspect for cracking of the fastener bores
between the sub-frame and frame 30, and
repair any crack before further flight in
accordance with paragraph 2.B. of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–173, Revision 2,
March 28, 2006. If the damage exceeds limits
specified in the SRM, before further flight,
contact BAE Systems and repair. Repeat the
inspection thereafter at intervals not to
exceed 4,000 flight cycles for the forward six
bolt bores, and 11,900 flight cycles for the
remaining fastener bores between the subframe and frame 30. Replacing the longeron
terminates the repetitive inspection
requirements of paragraphs (f)(4) and (f)(5) of
this AD; new inspections must be done in
accordance with this paragraph.
Note 4: The threshold for an aircraft is reset
if a replacement longeron is fitted.
FAA AD Differences
Note 5: This AD differs from the MCAI
and/ or service information as follows: The
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Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
MCAI specifies doing repetitive inspections
until the airplane enters the life extension
program (LEP). This program is not defined
by the FAA. Operators of airplanes that enter
the LEP may request an alternative method
of compliance (AMOC) for the repetitive
inspections in accordance with the
procedures specified in paragraph (g) of this
AD.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) AMOCs: The Manager, ANM–116,
Transport Airplane Directorate, International
Branch, 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, FAA, Transport Airplane
Directorate, 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.
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Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) Airworthiness
Directive 2006–0215, dated July 14, 2006,
and BAe Systems (Operations) Limited
Inspection Service Bulletin ISB.53–173,
Revision 2, dated March 28, 2006, for related
information.
Material Incorporated by Reference
(i) You must use BAe Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
173, Revision 2, dated March 28, 2006, 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
VerDate Aug<31>2005
17:40 Mar 11, 2008
Jkt 214001
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 February
28, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–4673 Filed 3–11–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0228; Directorate
Identifier 2007–NM–107–AD; Amendment
39–15421; AD 2008–06–09]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–200 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–200 series airplanes.
This AD requires repetitive inspections
to detect cracking of the support fittings
of the Krueger flap actuators, and
corrective actions if necessary. This AD
also requires eventual replacement of
any existing aluminum support fitting
on each wing with a steel fitting, and
modification of the aft attachment of the
actuator. Doing these actions terminates
the repetitive inspection requirements.
This AD results from reports of cracking
due to fatigue and stress corrosion of the
support fittings of the Krueger flap
actuator. We are issuing this AD to
prevent cracking of the support fittings,
which could result in fracturing of the
actuator attach lugs, separation of the
actuator from the support fitting,
severing of the hydraulic lines, resultant
loss of hydraulic fluids, and consequent
reduced controllability of the airplane.
DATES: This AD is effective April 16,
2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 16, 2008.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
PO 00000
Frm 00039
Fmt 4700
Sfmt 4700
13109
Examining the AD Docket
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.
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
certain Boeing Model 737–200 series
airplanes. That NPRM was published in
the Federal Register on November 26,
2007 (72 FR 65909). That NPRM
proposed to require repetitive
inspections to detect cracking of the
support fittings of the Krueger flap
actuators, and corrective actions if
necessary. The NPRM also proposed to
require eventual replacement of any
existing aluminum support fitting on
each wing with a steel fitting, and
modification of the aft attachment of the
actuator. Doing these actions terminates
the repetitive inspection requirements.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the one comment received.
Boeing supports the NPRM.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
There are about 13 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
E:\FR\FM\12MRR1.SGM
12MRR1
]]>Agencies
[Federal Register Volume 73, Number 49 (Wednesday, March 12, 2008)]
[Rules and Regulations]
[Pages 13106-13109]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-4673]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0368; Directorate Identifier 2007-NM-050-AD;
Amendment 39-15420; AD 2008-06-08]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited Model
BAe 146-100A, -200A, and -300A Series 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 product. The MCAI describes the unsafe condition as:
Cracking has been found on the centre fuselage top aft longeron
at Rib `0' on an in-service aircraft. * * *
This condition could result in reduced structural integrity of the
airplane. We are issuing this AD to require actions to correct the
unsafe condition on these products.
DATES: This AD becomes effective April 16, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 16,
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, FAA, Transport Airplane Directorate,
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 December 20, 2007
(72 FR 72270). That NPRM proposed to correct an unsafe condition for
the specified products. The MCAI states:
Cracking has been found on the centre fuselage top aft longeron
at Rib `0' on an in-service aircraft. Subsequent investigation has
indicated that the currently defined threshold and repeat inspection
period must be reduced, and the area of inspection expanded for the
BAe 146 series 100 and 200. For the BAe146 series 300, only the
repeat inspection period must be reduced, and the area of inspection
expanded.
Cracking on the center fuselage top aft longeron at Rib `0,' could
result in reduced structural integrity of the airplane. Corrective
actions include repetitive inspections of the center fuselage top aft
longeron for cracking and repair/replacement if necessary. 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.
Revision to the Reference to the Nondestructive Testing (NDT) Manual
We have removed the reference to the BAE Systems (Operations)
Limited BAe 146/Avro 146-RJ Series NDT Manual Part 6 20-00-03 from
paragraphs (f)(2)(iii) and (f)(5)(iii) of this AD. The appropriate
source of service information for doing the inspection and repair
specified in paragraphs (f)(2)(iii) and (f)(5)(iii) of this AD is BAE
Systems (Operations) Limited Inspection Service Bulletin ISB.53-173,
Revision 2, dated March 28, 2006. The Accomplishment Instructions of
the service bulletin refer to the NDT manual. We have added Note 1 and
Note 3 to this AD to clarify that the service bulletin refers to the
NDT manual as a secondary source of service information for doing the
inspection.
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 these changes 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.
[[Page 13107]]
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 1 product of U.S.
registry. We also estimate that it will take about 8 work-hours per
product to comply with the basic requirements of this AD. The average
labor rate is $80 per work-hour. Based on these figures, we estimate
the cost of this AD to the U.S. operators to be $640, or $640 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:
2008-06-08 BAE Systems (Operations) Limited (Formerly British
Aerospace Regional Aircraft): Amendment 39-15420. Docket No. FAA-
2007-0368; Directorate Identifier 2007-NM-050-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
16, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model BAe 146-100A, -200A, and -300A series airplanes; certificated
in any category.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Cracking has been found on the centre fuselage top aft longeron
at Rib `0' on an in-service aircraft. Subsequent investigation has
indicated that the currently defined threshold and repeat inspection
period must be reduced, and the area of inspection expanded for the
BAe 146 series 100 and 200. For the BAe 146 series 300, only the
repeat inspection period must be reduced, and the area of inspection
expanded.
Cracking on the center fuselage top aft longeron at Rib `0' could
result in reduced structural integrity of the airplane. Corrective
actions include repetitive inspections of the center fuselage top
aft longeron for cracking and repair/replacement if necessary.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) For all Model BAe 146-100A and BAE 146-200A series airplanes
pre-mod HCM01709B or HCM01709C that have not been inspected in
accordance with BAE Systems (Operations) Limited BAe 146 Maintenance
Review Board Report (MRBR) SSI/SII Task No. 53-20-140A (Maintenance
Planning Document (MPD) Task 532040-SDI-10000-3) or BAE Systems
(Operations) Limited Inspection Service Bulletin ISB.53-173,
Revision 1, dated May 19, 2004, as of the effective date of this AD:
Do the actions in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD at
the applicable compliance time, and do all applicable repairs and
replacements before further flight.
(i) Inspect and repair cracking of the forward six bolt bores
between the subframe and frame 30 in accordance with paragraph 2.B
of the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53-173, Revision 2, dated
March 28, 2006, before the accumulation of 17,000 total flight
cycles, or within 500 flight cycles after the effective date of this
AD, whichever occurs later. If the damage exceeds limits specified
in the structural repair manual (SRM), before further flight,
contact BAE Systems and repair. Repeat the inspection thereafter at
intervals not to exceed 5,000 flight cycles, except as provided by
paragraph (f)(3) of this AD.
(ii) Inspect and repair cracking of the remaining fastener bores
between the sub-frame and frame 30 in accordance with paragraph 2.B
of the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53-173, Revision 2, dated
March 28, 2006, before the accumulation of 17,000 total flight
cycles, or within 4,000 flight cycles after the effective date of
this AD, whichever occurs later. If the damage exceeds limits
specified in the SRM, before further flight, contact BAE Systems and
repair. Repeat the inspection thereafter at intervals not to exceed
11,900 flight cycles, except as provided by paragraph (f)(3) of this
AD.
(2) For all Model BAe 146-100A and BAe 146-200A series airplanes
pre-mod HCM01709B or HCM01709C that have been inspected in
accordance with BAE Systems (Operations) Limited BAe 146 MRBR SSI/
SII Task No. 53-20-140A (MPD task 532040-SDI-10000-3) or BAE Systems
(Operations) Limited Inspection Service Bulletin ISB.53-173 Revision
1, May 19, 2004, as of the effective date of this AD: Do the actions
in paragraphs (f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of this AD at
the applicable compliance time, and do all applicable repairs and
replacements before further flight.
(i) Do an ultrasonic inspection and repair cracking of the
forward six bolt bores between the subframe and frame 30 in
[[Page 13108]]
accordance with paragraph 2.B of the Accomplishment Instructions and
Appendix 2 of BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.53-173, Revision 2, dated March 28, 2006, before the
accumulation of 5,400 flight cycles since last inspection, or within
500 flight cycles after the effective date of this AD, whichever
occurs later. If the damage exceeds limits specified in the SRM,
before further flight, contact BAE Systems and repair. Repeat the
inspection thereafter at intervals not to exceed 5,000 flight
cycles, except as provided by paragraph (f)(3) of this AD.
(ii) Do a high frequency eddy current inspection and repair
cracking of the forward six bolt bores between the subframe and
frame 30 in accordance with paragraph 2.B of the Accomplishment
Instructions and Appendix 3 of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-173, Revision 2, dated March 28,
2006, within 4,000 flight cycles after the effective date of this
AD. If the damage exceeds limits specified in the SRM, before
further flight, contact BAE systems and repair. Repeat the
inspection thereafter at intervals not to exceed 5,000 flight
cycles, except as provided by paragraph (f)(3) of this AD.
(iii) Do a rotating eddy current inspection and repair cracking
of the remaining fastener bores between the sub-frame and frame 30
in accordance with paragraph 2.B of the Accomplishment Instructions
of BAE Systems (Operations) Limited Inspection Service Bulletin
ISB.53-173, Revision 2, dated March 28, 2006, within 4,000 flight
cycles after the effective date of this AD. If the damage exceeds
limits specified in the SRM, before further flight, contact BAE
Systems and repair. Repeat the inspection thereafter at intervals
not to exceed 11,900 flight cycles, except as provided by paragraph
(f)(3) of this AD.
Note 1: BAE Systems (Operations) Limited Inspection Service
Inspection Bulletin ISB.53-173, Revision 2, dated March 28, 2006,
refers to the BAE Systems (Operations) Limited BAe 146/Avro 146-RJ
Series Nondestructive Testing (NDT) Manual Part 6 20-00-03 as a
secondary source of service information for doing the eddy current
inspection.
(3) For all Model BAe 146-100A and BAe 146-200A series airplanes
pre-mod HCM01709B or HCM01709C that have had a replacement aft
longeron installed: Prior to the accumulation of 17,000 flight
cycles after the aft longeron replacement, or within 500 flight
cycles after the effective date of this AD, whichever occurs later,
inspect for cracking of the forward six bolt bores and the fastener
bores between the sub-frame and frame 30, and repair any crack
before further flight in accordance with paragraph 2.B of the
Accomplishment Instructions of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-173, Revision 2, dated March 28,
2006. If the damage exceeds limits specified in the SRM, before
further flight, contact BAE Systems and repair. Repeat the
inspection thereafter at intervals not to exceed 5,000 flight cycles
for the forward six bolt bores, and 11,900 flight cycles for the
remaining fastener bores between the sub-frame and frame 30.
Replacing the longeron terminates the repetitive inspection
requirements of paragraph (f)(1) and (f)(2) of this AD; post-
replacement inspections must be done in accordance with this
paragraph.
Note 2: The threshold for an aircraft is reset if a replacement
longeron is fitted.
(4) For all Model BAe 146-300A series airplanes pre-mod
HCM01709A that have not been inspected in accordance with BAE
Systems (Operations) Limited BAe 146 MRBR SSI/SII Task No. 53-20-
140A (MPD Task 532040-SDI-10000-3) or BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53-173, Revision 1, dated
May 19, 2004, as of the effective date of this AD: Do the actions in
paragraphs (f)(4)(i) and (f)(4)(ii) of this AD at the applicable
compliance time, and do all applicable repairs and replacements
before further flight.
(i) Inspect and repair cracking of the forward six bolt bores
between the subframe and frame 30 in accordance with paragraph 2.B
of the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53-173, Revision 2, dated
March 28, 2006, prior to the accumulation of 24,000 total flight
cycles, or within 500 flight cycles after the effective date of this
AD, whichever occurs later. If the damage exceeds limits specified
in the SRM, before further flight, contact BAE Systems and repair.
Repeat the inspection thereafter at intervals not to exceed 4,000
flight cycles, except as provided by paragraph (f)(6) of this AD.
(ii) Inspect and repair cracking of the remaining fastener bores
between the sub-frame and frame 30 in accordance with paragraph 2.B
of the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53-173, Revision 2, dated
March 28, 2006, at the later of 24,000 total flight cycles, or
within 4,000 flight cycles after the effective date of this AD. If
the damage exceeds limits specified in the SRM, before further
flight, contact BAE Systems and repair. Repeat the inspection
thereafter at intervals not to exceed 11,900 flight cycles, except
as provided by paragraph (f)(6) of this AD.
(5) For all Model BAe 146-300A series airplanes pre-mod
HCM01709A that have been inspected in accordance with BAE Systems
(Operations) Limited BAe 146 MRBR SSI/SII Task No. 53-20-140A (MPD
task 532040-SDI-10000-3) or BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-173, Revision 1, May 19, 2004, as
of the effective date of this AD: Do the actions in paragraphs
(f)(5)(i), (f)(5)(ii), and (f)(5)(iii) of this AD at the applicable
compliance time, and do all applicable repairs and replacements
before further flight.
(i) Do an ultrasonic inspection and repair cracking of the
forward six bores between the subframe and frame 30 in accordance
with paragraph 2.B of the Accomplishment Instructions and Appendix 2
of BAE Systems (Operations) Limited Inspection Service Bulletin
ISB.53-173, Revision 2, dated March 28, 2006, within 4,000 flight
cycles since last inspection, or within 500 flight cycles after the
effective date of this AD, whichever occurs later. If the damage
exceeds limits specified in the SRM, before further flight, contact
BAE Systems and repair. Repeat the inspection thereafter at
intervals not to exceed 4,000 flight cycles except as provided by
paragraph (f)(6) of this AD.
(ii) Do a high frequency eddy current inspection and repair
cracking of the forward six bolt bores between the subframe and
frame 30 in accordance with paragraph 2.B of the Accomplishment
Instructions and Appendix 3 of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-173, Revision 2, dated March 28,
2006, within 4,000 flight cycles after the effective date of this
AD. If the damage exceeds limits specified in the SRM, before
further flight, contact BAE Systems and repair. Repeat the
inspection thereafter at intervals not to exceed 4,000 flight
cycles, except as provided by paragraph (f)(6) of this AD.
(iii) Do a rotating eddy current inspection and repair cracking
of the remaining fastener bores between the sub-frame and frame 30
in accordance with paragraph 2.B of the Accomplishment Instructions
of BAE Systems (Operations) Limited Inspection Service Bulletin
ISB.53-173, Revision 2, dated March 28, 2006, within 4,000 flight
cycles after the effective date of this AD. If the damage exceeds
limits specified in the SRM, before further flight, contact BAE
Systems and repair. Repeat the inspection thereafter at intervals
not to exceed 11,900 flight cycles, except as provided by paragraph
(f)(6) of this AD.
Note 3: BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.53-173, Revision 2, dated March 28, 2006, refers to the
BAE Systems (Operations) Limited BAe 146/Avro 146-RJ Series NDT
Manual Part 6 20-00-03 as a secondary source of service information
for doing the eddy current inspection.
(6) For all Model BAe 146-300A series airplanes pre-mod
HCM01709A that have had a replacement aft longeron installed: Prior
to the accumulation of 24,000 flight cycles after the aft longeron
replacement, or within 500 flight cycles after the effective date of
this AD, whichever occurs later, inspect for cracking of the
fastener bores between the sub-frame and frame 30, and repair any
crack before further flight in accordance with paragraph 2.B. of the
Accomplishment Instructions of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-173, Revision 2, March 28, 2006.
If the damage exceeds limits specified in the SRM, before further
flight, contact BAE Systems and repair. Repeat the inspection
thereafter at intervals not to exceed 4,000 flight cycles for the
forward six bolt bores, and 11,900 flight cycles for the remaining
fastener bores between the sub-frame and frame 30. Replacing the
longeron terminates the repetitive inspection requirements of
paragraphs (f)(4) and (f)(5) of this AD; new inspections must be
done in accordance with this paragraph.
Note 4: The threshold for an aircraft is reset if a replacement
longeron is fitted.
FAA AD Differences
Note 5: This AD differs from the MCAI and/ or service
information as follows: The
[[Page 13109]]
MCAI specifies doing repetitive inspections until the airplane
enters the life extension program (LEP). This program is not defined
by the FAA. Operators of airplanes that enter the LEP may request an
alternative method of compliance (AMOC) for the repetitive
inspections in accordance with the procedures specified in paragraph
(g) of this AD.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) AMOCs: The Manager, ANM-116, Transport Airplane Directorate,
International Branch, 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, FAA, Transport Airplane Directorate,
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 European Aviation Safety Agency (EASA)
Airworthiness Directive 2006-0215, dated July 14, 2006, and BAe
Systems (Operations) Limited Inspection Service Bulletin ISB.53-173,
Revision 2, dated March 28, 2006, for related information.
Material Incorporated by Reference
(i) You must use BAe Systems (Operations) Limited Inspection
Service Bulletin ISB.53-173, Revision 2, dated March 28, 2006, 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 February 28, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-4673 Filed 3-11-08; 8:45 am]
BILLING CODE 4910-13-P
