Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A Airplanes, 27419-27422 [2010-11182]
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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
Note 4: Notwithstanding any other
maintenance or operational requirements,
components that have been identified as
airworthy or installed on the affected
airplanes before the revision of the ALS, as
required by paragraphs (f)(2) and (f)(3) of this
AD, do not need to be reworked in
accordance with the CDCCLs. However, once
the ALS has been revised, future
maintenance actions on these components
must be done in accordance with the
CDCCLs.
FAA AD Differences
Note 5: 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, New York Aircraft
Certification Office (ACO), ANE–170, 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:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York,
11590; telephone 516–228–7300; fax 516–
794–5531. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(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
(44 U.S.C. 3501 et seq.), 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 Canadian Airworthiness
Directive CF–2009–09, dated March 9, 2009;
Bombardier Service Bulletin 670BA–29–005,
Revision A, dated January 29, 2009; and
Bombardier TR 2–268 and Bombardier TR 2–
269, both dated December 18, 2008, both to
Section 3, ‘‘Fuel System Limitations,’’ of Part
2 of the Bombardier CL–600–2C10, CL–600–
2D15, and CL–600–2D24 Maintenance
Requirements Manual; for related
information.
Material Incorporated by Reference
(i) You must use the applicable service
information specified in Table 2 of this AD,
to do the actions required by this AD, unless
the AD specifies otherwise.
TABLE 2—MATERIAL INCORPORATED BY REFERENCE
Document
Revision
Date
Bombardier Service Bulletin 670BA–29–005 ......................................................................................
Bombardier Temporary Revision 2–268 to Section 3, ‘‘Fuel System Limitations,’’ of Part 2 of the
Bombardier CL–600–2C10, CL–600–2D15, and CL–600–2D24 Maintenance Requirements
Manual.
Bombardier Temporary Revision 2–269 to Section 3, ‘‘Fuel System Limitations,’’ of Part 2 of the
Bombardier CL–600–2C10, CL–600–2D15, and CL–600–2D24 Maintenance Requirements
Manual.
A ..............................
Original ....................
January 29, 2009.
December 18, 2008.
Original ....................
December 18, 2008.
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(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
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference 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 May 3,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–11183 Filed 5–14–10; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1254; Directorate
Identifier 2009–NM–040–AD; Amendment
39–16292; AD 2010–10–13]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited Model
BAe 146 and Avro 146–RJ70A, 146–
RJ85A, and 146–RJ100A 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:
During the removal of the wing removable
leading edge on a BAe 146 aircraft for a
repair (not related to the subject addressed by
PO 00000
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this AD), corrosion was found on the wing
fixed leading edge structure. The
investigation determined that the existing
scheduled environmental and fatigue
inspections would not have detected the
corrosion or fatigue damage.
Corrosion or fatigue damage in this area, if
not detected and corrected, could lead to
degradation of the structural integrity of the
wing.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective June
21, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 21, 2010.
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,
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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
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 January 12, 2010 (75 FR
1560). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
During the removal of the wing removable
leading edge on a BAe 146 aircraft for a
repair (not related to the subject addressed by
this AD), corrosion was found on the wing
fixed leading edge structure. The
investigation determined that the existing
scheduled environmental and fatigue
inspections would not have detected the
corrosion or fatigue damage.
Corrosion or fatigue damage in this area, if
not detected and corrected, could lead to
degradation of the structural integrity of the
wing.
For the reason described above, this AD
requires repetitive inspections of the wing
fixed leading edge and front spar structure
for corrosion and/or fatigue damage [e.g.,
cracking] and repair, depending on findings.
There are two alternative inspection
methods: Method 1 is a combination of
a detailed visual inspection and a visual
inspection; Method 2 is a detailed visual
inspection. 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 Compliance Time
Language
We have revised paragraph (f)(1)(iii)
of this AD to clarify the compliance
time language as specified in Note 4 of
this AD.
Conclusion
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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
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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.
Explanation of Change to Costs of
Compliance
Since issuance of the NPRM, we have
increased the labor rate used in the
Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of
Compliance information, below, reflects
this increase in the specified hourly
labor rate.
Costs of Compliance
We estimate that this AD will affect 1
product of U.S. registry. We also
estimate that it will take about 12 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operator to
be $1,020.
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.
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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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2010–10–13 BAE Systems (Operations)
Limited: Amendment 39–16292. Docket
No. FAA–2009–1254; Directorate
Identifier 2009–NM–040–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective June 21, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to BAE Systems
(Operations) Limited Model BAe 146–100A,
–200A, and –300A series airplanes; and
Model Avro 146–RJ70A, 146–RJ85A, and
146–RJ100A airplanes; certificated in any
category, all serial numbers.
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Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
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Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During the removal of the wing removable
leading edge on a BAe 146 aircraft for a
repair (not related to the subject addressed by
this AD), corrosion was found on the wing
fixed leading edge structure. The
investigation determined that the existing
scheduled environmental and fatigue
inspections would not have detected the
corrosion or fatigue damage.
Corrosion or fatigue damage in this area, if
not detected and corrected, could lead to
degradation of the structural integrity of the
wing.
For the reason described above, this AD
requires repetitive inspections of the wing
fixed leading edge and front spar structure
for corrosion and/or fatigue damage [e.g.,
cracking] and repair, depending on findings.
There are two alternative inspection
methods: Method 1 is a combination of a
detailed visual inspection and a visual
inspection; Method 2 is a detailed visual
inspection.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) At the applicable time identified in
paragraph (f)(1)(i), (f)(1)(ii), or (f)(1)(iii) of
this AD: Perform a detailed visual inspection
and visual inspection (Method 1) or a
detailed visual inspection (Method 2) for
cracking and corrosion of the wing fixed
leading edge and front spar structure, in
accordance with paragraph 2.C. or 2.D., as
applicable, of the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.57–
072, Revision 1, dated September 25, 2008.
(i) For airplanes with less than 9 years
since date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness as of the effective date of this
AD: Within 18 months after the effective date
of this AD.
(ii) For airplanes with 9 years or more, but
less than 15 years, since date of issuance of
the original airworthiness certificate or the
date of issuance of the original export
certificate of airworthiness as of the effective
date of this AD: Within 18 months after the
effective date of this AD or within 16 years
since date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness, whichever occurs first.
(iii) For airplanes with 15 years or more
since date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness as of the effective date of this
AD: Within 6 months after the effective date
of this AD.
Note 1: Where BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.57–
072, Revision 1, dated September 25, 2008,
refers to a ‘‘visual inspection,’’ this term
describes an inspection using visual
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inspection equipment as defined in
Appendix 3 of that service bulletin. In other
BAE Systems instructions for continued
airworthiness, including the Maintenance
Planning Document (MPD) and the Corrosion
Prevention and Control Programme (CPCP),
such an inspection is referred to as a ‘‘Special
Detailed Inspection’’ (SDI).
Note 2: At the discretion of the airplane
owner/operator, corrosion protection may be
embodied on those areas subject to a detailed
visual inspection, in accordance with
paragraph 2.E. or paragraph 2.F. of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.57–072, Revision 1,
dated September 25, 2008. Embodiment of
enhanced corrosion protection in accordance
with paragraph 2.E. of the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.57–
072, Revision 1, dated September 25, 2008,
allows the interval of the repetitive
inspection (as required by paragraph (f)(2) of
this AD) to be extended in the area(s) of
application in accordance with paragraph
(f)(2)(i) or (f)(2)(ii) of this AD, as applicable.
(2) After doing the initial inspection
required by paragraph (f)(1) of this AD, at the
applicable intervals specified in paragraph
(f)(2)(i) or (f)(2)(ii) of this AD, accomplish the
repetitive inspections of the wing fixed
leading edge and front spar structure for
cracking and corrosion in the ‘‘area of
inspection’’ specified in Table 1 of paragraph
1.D., ‘‘Compliance,’’ of BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.57–072, Revision 1, dated
September 25, 2008. Do the inspections in
accordance with paragraph 2.C. (Method 1)
or paragraph 2.D. (Method 2) of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.57–072, Revision 1,
dated September 25, 2008. Where previously
applied, enhanced corrosion protection may
then be re-applied, as an option, in
accordance with paragraph 2.E. of the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.57–072, Revision 1,
dated September 25, 2008. Perform the
repetitive inspections at the times specified
in paragraph (f)(2)(i) or (f)(2)(ii) of this AD,
as applicable.
(i) For airplanes having enhanced
corrosion protection that was applied during
the previous inspection: Inspect at intervals
not to exceed 144 months.
(ii) For airplanes not having enhanced
corrosion protection that was applied during
the previous inspection: Inspect at intervals
not to exceed 72 months.
(3) After doing the initial inspection
required by paragraph (f)(1) of this AD, at
intervals not to exceed 36,000 flight cycles,
accomplish fatigue inspections in accordance
with paragraph 2.C. (Method 1) or paragraph
2.D. (Method 2) of the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.57–
072, Revision 1, dated September 25, 2008.
(4) If any cracking or corrosion is found
during any inspection required by this AD,
before further flight, repair in accordance
with the Accomplishment Instructions of
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27421
BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.57–072,
Revision 1, dated September 25, 2008.
(5) No repair terminates the inspection
requirements of this AD.
(6) Actions done before the effective date
of this AD in accordance with BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.57–072, dated February 22,
2008, are considered acceptable for
compliance with the corresponding actions
specified in this AD.
(7) Submit a report of the findings (both
positive and negative) of the inspection
required by paragraph (f)(1) of this AD to
Customer Liaison, Customer Support
(Building 37), BAE Systems (Operations)
Limited, Prestwick International Airport,
Ayrshire, KA9 2RW, Scotland; fax +44 (0)
1292 675432; e-mail
raengliaison@baesystems.com, at the
applicable time specified in paragraphs
(f)(7)(i) and (f)(7)(ii) of this AD. The report
must include the inspection results, a
description of any discrepancies found, the
airplane serial number, and the number of
landings and flight hours on the airplane.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
Note 3: The inspections required by this
AD prevail over the Maintenance Review
Board Report (MRBR), MPD, CPCP, and
Supplemental Structural Inspection
Document (SSID) inspections defined in
paragraph 1.C.(3) of BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.57–072, Revision 1, dated
September 25, 2008.
FAA AD Differences
Note 4: This AD differs from the MCAI
and/or service information as follows: Where
the EASA AD refers to ‘‘since entry into
service,’’ this AD specifies the date of
issuance of the original airworthiness
certificate or the date of issuance of the
original export certificate of airworthiness.
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
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
The AMOC approval letter must specifically
reference this AD.
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Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
(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
(44 U.S.C. 3501 et seq.), 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 Airworthiness Directive 2009–
0014, dated January 21, 2009; and BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.57–072, Revision 1,
dated September 25, 2008; for related
information.
Material Incorporated by Reference
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(i) You must use BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.57–
072, Revision 1, dated September 25, 2008,
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 BAE Systems Regional
Aircraft, 13850 McLearen Road, Herndon,
Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet
https://www.baesystems.com/Businesses/
RegionalAircraft/index.htm.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference 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 April 30,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–11182 Filed 5–14–10; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0158; Directorate
Identifier 2010–CE–006–AD; Amendment
39–16289; AD 2010–10–10]
RIN 2120–AA64
Airworthiness Directives; Hawker
Beechcraft Corporation (Type
Certificate No. A00010WI Previously
Held by Raytheon Aircraft Company)
Model 390 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Hawker Beechcraft Corporation Model
390 airplanes. This AD requires you to
inspect the essential bus lightning strike
protection for proper installation of
metal oxide varistor (MOV) and spark
gap wiring. This AD also requires you
to rework the wiring as necessary to
achieve the required lightning strike/
surge protection. This AD results from
a report that the wires to the MOV and
spark gap were swapped. We are issuing
this AD to detect and correct improper
installation of the MOV and spark gap
wiring, which could result in overload
of the MOV in a lightning strike and
allow electrical energy to continue to
the essential bus and disable equipment
that receives power from the essential
bus. The disabled equipment could
include the autopilot, anti-skid system,
hydraulic indicator, spoiler system,
pilot primary flight display, audio
panel, or the #1 air data computer. This
failure could lead to a significant
increase in pilot workload during
adverse operating conditions.
DATES: This AD becomes effective on
June 21, 2010.
On June 21, 2010, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: For service information
identified in this AD, contact Hawker
Beechcraft Corporation, 9709 East
Central, Wichita, Kansas 67201;
telephone: (316) 676–5034; fax: (316)
676–6614; Internet: https://
www.hawkerbeechcraft.com/
service_support/pubs/.
To view the AD docket, go to U.S.
Department of Transportation, Docket
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Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2010–0158; Directorate
Identifier 2010–CE–006–AD.
FOR FURTHER INFORMATION CONTACT:
Kevin Schwemmer, Aerospace Engineer,
FAA, Wichita Aircraft Certification
Office (ACO), 1801 Airport Road, Room
100, Wichita, Kansas 67209; telephone:
(316) 946–4174; fax: (316) 946–4107;
e-mail: kevin.schwemmer@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On February 16, 2010, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Hawker Beechcraft Corporation
Model 390 airplanes. This proposal was
published in the Federal Register as a
notice of proposed rulemaking (NPRM)
on February 23, 2010 (75 FR 8001). The
NPRM proposed to require you to
inspect the essential bus lightning strike
protection for proper installation of
metal oxide varistor (MOV) and spark
gap wiring. The NPRM also proposed to
require you to rework the wiring as
necessary to achieve the required
lightning strike/surge protection.
Comments
We provided the public the
opportunity to participate in developing
this AD. We received no comments on
the proposal or on the determination of
the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 170
airplanes in the U.S. registry.
We estimate the following costs to do
the inspection (includes any necessary
follow-on action):
E:\FR\FM\17MYR1.SGM
17MYR1
]]>Agencies
[Federal Register Volume 75, Number 94 (Monday, May 17, 2010)]
[Rules and Regulations]
[Pages 27419-27422]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-11182]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-1254; Directorate Identifier 2009-NM-040-AD;
Amendment 39-16292; AD 2010-10-13]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited Model
BAe 146 and Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A 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:
During the removal of the wing removable leading edge on a BAe
146 aircraft for a repair (not related to the subject addressed by
this AD), corrosion was found on the wing fixed leading edge
structure. The investigation determined that the existing scheduled
environmental and fatigue inspections would not have detected the
corrosion or fatigue damage.
Corrosion or fatigue damage in this area, if not detected and
corrected, could lead to degradation of the structural integrity of
the wing.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective June 21, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 21,
2010.
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,
[[Page 27420]]
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 January 12, 2010 (75
FR 1560). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During the removal of the wing removable leading edge on a BAe
146 aircraft for a repair (not related to the subject addressed by
this AD), corrosion was found on the wing fixed leading edge
structure. The investigation determined that the existing scheduled
environmental and fatigue inspections would not have detected the
corrosion or fatigue damage.
Corrosion or fatigue damage in this area, if not detected and
corrected, could lead to degradation of the structural integrity of
the wing.
For the reason described above, this AD requires repetitive
inspections of the wing fixed leading edge and front spar structure
for corrosion and/or fatigue damage [e.g., cracking] and repair,
depending on findings.
There are two alternative inspection methods: Method 1 is a combination
of a detailed visual inspection and a visual inspection; Method 2 is a
detailed visual inspection. 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 Compliance Time Language
We have revised paragraph (f)(1)(iii) of this AD to clarify the
compliance time language as specified in Note 4 of this AD.
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.
Explanation of Change to Costs of Compliance
Since issuance of the NPRM, we have increased the labor rate used
in the Costs of Compliance from $80 per work-hour to $85 per work-hour.
The Costs of Compliance information, below, reflects this increase in
the specified hourly labor rate.
Costs of Compliance
We estimate that this AD will affect 1 product of U.S. registry. We
also estimate that it will take about 12 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operator to be $1,020.
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:
2010-10-13 BAE Systems (Operations) Limited: Amendment 39-16292.
Docket No. FAA-2009-1254; Directorate Identifier 2009-NM-040-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 21,
2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to BAE Systems (Operations) Limited Model
BAe 146-100A, -200A, and -300A series airplanes; and Model Avro 146-
RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any
category, all serial numbers.
[[Page 27421]]
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During the removal of the wing removable leading edge on a BAe
146 aircraft for a repair (not related to the subject addressed by
this AD), corrosion was found on the wing fixed leading edge
structure. The investigation determined that the existing scheduled
environmental and fatigue inspections would not have detected the
corrosion or fatigue damage.
Corrosion or fatigue damage in this area, if not detected and
corrected, could lead to degradation of the structural integrity of
the wing.
For the reason described above, this AD requires repetitive
inspections of the wing fixed leading edge and front spar structure
for corrosion and/or fatigue damage [e.g., cracking] and repair,
depending on findings.
There are two alternative inspection methods: Method 1 is a
combination of a detailed visual inspection and a visual inspection;
Method 2 is a detailed visual inspection.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) At the applicable time identified in paragraph (f)(1)(i),
(f)(1)(ii), or (f)(1)(iii) of this AD: Perform a detailed visual
inspection and visual inspection (Method 1) or a detailed visual
inspection (Method 2) for cracking and corrosion of the wing fixed
leading edge and front spar structure, in accordance with paragraph
2.C. or 2.D., as applicable, of the Accomplishment Instructions of
BAE Systems (Operations) Limited Inspection Service Bulletin ISB.57-
072, Revision 1, dated September 25, 2008.
(i) For airplanes with less than 9 years since date of issuance
of the original airworthiness certificate or the date of issuance of
the original export certificate of airworthiness as of the effective
date of this AD: Within 18 months after the effective date of this
AD.
(ii) For airplanes with 9 years or more, but less than 15 years,
since date of issuance of the original airworthiness certificate or
the date of issuance of the original export certificate of
airworthiness as of the effective date of this AD: Within 18 months
after the effective date of this AD or within 16 years since date of
issuance of the original airworthiness certificate or the date of
issuance of the original export certificate of airworthiness,
whichever occurs first.
(iii) For airplanes with 15 years or more since date of issuance
of the original airworthiness certificate or the date of issuance of
the original export certificate of airworthiness as of the effective
date of this AD: Within 6 months after the effective date of this
AD.
Note 1: Where BAE Systems (Operations) Limited Inspection
Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008,
refers to a ``visual inspection,'' this term describes an inspection
using visual inspection equipment as defined in Appendix 3 of that
service bulletin. In other BAE Systems instructions for continued
airworthiness, including the Maintenance Planning Document (MPD) and
the Corrosion Prevention and Control Programme (CPCP), such an
inspection is referred to as a ``Special Detailed Inspection''
(SDI).
Note 2: At the discretion of the airplane owner/operator,
corrosion protection may be embodied on those areas subject to a
detailed visual inspection, in accordance with paragraph 2.E. or
paragraph 2.F. of the Accomplishment Instructions of BAE Systems
(Operations) Limited Inspection Service Bulletin ISB.57-072,
Revision 1, dated September 25, 2008. Embodiment of enhanced
corrosion protection in accordance with paragraph 2.E. of the
Accomplishment Instructions of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.57-072, Revision 1, dated September
25, 2008, allows the interval of the repetitive inspection (as
required by paragraph (f)(2) of this AD) to be extended in the
area(s) of application in accordance with paragraph (f)(2)(i) or
(f)(2)(ii) of this AD, as applicable.
(2) After doing the initial inspection required by paragraph
(f)(1) of this AD, at the applicable intervals specified in
paragraph (f)(2)(i) or (f)(2)(ii) of this AD, accomplish the
repetitive inspections of the wing fixed leading edge and front spar
structure for cracking and corrosion in the ``area of inspection''
specified in Table 1 of paragraph 1.D., ``Compliance,'' of BAE
Systems (Operations) Limited Inspection Service Bulletin ISB.57-072,
Revision 1, dated September 25, 2008. Do the inspections in
accordance with paragraph 2.C. (Method 1) or paragraph 2.D. (Method
2) of the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated
September 25, 2008. Where previously applied, enhanced corrosion
protection may then be re-applied, as an option, in accordance with
paragraph 2.E. of the Accomplishment Instructions of BAE Systems
(Operations) Limited Inspection Service Bulletin ISB.57-072,
Revision 1, dated September 25, 2008. Perform the repetitive
inspections at the times specified in paragraph (f)(2)(i) or
(f)(2)(ii) of this AD, as applicable.
(i) For airplanes having enhanced corrosion protection that was
applied during the previous inspection: Inspect at intervals not to
exceed 144 months.
(ii) For airplanes not having enhanced corrosion protection that
was applied during the previous inspection: Inspect at intervals not
to exceed 72 months.
(3) After doing the initial inspection required by paragraph
(f)(1) of this AD, at intervals not to exceed 36,000 flight cycles,
accomplish fatigue inspections in accordance with paragraph 2.C.
(Method 1) or paragraph 2.D. (Method 2) of the Accomplishment
Instructions of BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.57-072, Revision 1, dated September 25, 2008.
(4) If any cracking or corrosion is found during any inspection
required by this AD, before further flight, repair in accordance
with the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated
September 25, 2008.
(5) No repair terminates the inspection requirements of this AD.
(6) Actions done before the effective date of this AD in
accordance with BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.57-072, dated February 22, 2008, are considered
acceptable for compliance with the corresponding actions specified
in this AD.
(7) Submit a report of the findings (both positive and negative)
of the inspection required by paragraph (f)(1) of this AD to
Customer Liaison, Customer Support (Building 37), BAE Systems
(Operations) Limited, Prestwick International Airport, Ayrshire, KA9
2RW, Scotland; fax +44 (0) 1292 675432; e-mail
raengliaison@baesystems.com, at the applicable time specified in
paragraphs (f)(7)(i) and (f)(7)(ii) of this AD. The report must
include the inspection results, a description of any discrepancies
found, the airplane serial number, and the number of landings and
flight hours on the airplane.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
Note 3: The inspections required by this AD prevail over the
Maintenance Review Board Report (MRBR), MPD, CPCP, and Supplemental
Structural Inspection Document (SSID) inspections defined in
paragraph 1.C.(3) of BAE Systems (Operations) Limited Inspection
Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008.
FAA AD Differences
Note 4: This AD differs from the MCAI and/or service
information as follows: Where the EASA AD refers to ``since entry
into service,'' this AD specifies the date of issuance of the
original airworthiness certificate or the date of issuance of the
original export certificate of airworthiness.
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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
[[Page 27422]]
(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 (44
U.S.C. 3501 et seq.), 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 Airworthiness
Directive 2009-0014, dated January 21, 2009; and BAE Systems
(Operations) Limited Inspection Service Bulletin ISB.57-072,
Revision 1, dated September 25, 2008; for related information.
Material Incorporated by Reference
(i) You must use BAE Systems (Operations) Limited Inspection
Service Bulletin ISB.57-072, Revision 1, dated September 25, 2008,
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 BAE
Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia
20171; telephone 703-736-1080; e-mail raebusiness@baesystems.com;
Internet https://www.baesystems.com/Businesses/RegionalAircraft/index.htm.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(4) You may also review copies of the service information that
is incorporated by reference 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 April 30, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-11182 Filed 5-14-10; 8:45 am]
BILLING CODE 4910-13-P
