Airworthiness Directives; British Aerospace Regional Aircraft Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 Airplanes, 36914-36916 [E7-13091]
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36914
Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules
Models
Serial Nos.
(4) V35B .............................................................
(5) A36 ................................................................
(6) A36TC and B36TC .......................................
(7) 95–B55 ..........................................................
(8) D55 ...............................................................
(9) E55 ................................................................
(10) A56TC .........................................................
(11) 58 ................................................................
(12) 58P ..............................................................
(13) 58TC ...........................................................
(14) G58 .............................................................
D–9069 through D–10403.
E–185 through E–3629 and E–3631 through E–3635.
EA–1 through EA–695.
TC–1913, TC–1936 through TC–2456.
TE–452 through TE–767.
TE–768 through TE–1201.
TG–84 through TG–94.
TH–1 through TH–2124.
TJ–3 through TJ–497.
TK–1 through TK–151.
TH–2126, TH–2127, TH–2131 through TH–2134, TH–2136, TH–2137, TH–2139 through TH–
2141, and TH–2143 through TH–2150.
WA–1 through WA–312.
(15) 77 ................................................................
Unsafe Condition
(d) This AD results from reports of certain
circuit breaker toggle switches used in
various electrical systems through the
affected airplanes overheating. We are
proposing this AD to prevent failure of the
circuit breaker toggle switch, which could
result in smoke in the cockpit and the
inability to turn off the switch.
Compliance
(e) To address this problem, you must do
the following, unless already done:
Actions
Compliance
Procedures
(1) Replace all affected circuit breaker toggle
switches specified in paragraph (c) of this
AD with an improved circuit breaker toggle
switch, P/N 35–380132–61 through 35–
380132–113, as applicable.
(2) Do not install a circuit breaker toggle switch
specified in paragraph (c) of this AD.
Within the next 12 months after the effective
date of this AD.
As specified in Hawker Beechcraft Recommended Service Bulletin SB 24–3807,
Issued: May, 2007, and Raytheon Aircraft
Company Recommended Service Bulletin
SB 24–3735, Issued: August, 2005.
Not applicable.
Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(f) The Manager, Wichita Aircraft
Certification Office (ACO), 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: Jose
Flores, Aviation Safety Engineer, FAA,
Wichita ACO, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946–
4132; fax: (316) 946–4107. 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.
Federal Aviation Administration
Related Information
rmajette on PROD1PC64 with PROPOSALS
(g) To get copies of the service information
referenced in this AD, contact Hawker
Beechcraft Corporation, 9709 East Central,
Wichita, Kansas 67291; telephone: (800) 429–
5372 or (316) 676–3140. To view the AD
docket, go to U.S. Department of
Transportation, Docket Operations, M–30,
West Building Ground Floor, Room W12–
140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, or on the Internet at
https://dms.dot.gov. The docket number is
Docket No. FAA–2007–28434; Directorate
Identifier 2007–CE–053–AD.
Issued in Kansas City, Missouri, on June
29, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–13088 Filed 7–5–07; 8:45 am]
BILLING CODE 4910–13–P
VerDate Aug<31>2005
15:50 Jul 05, 2007
Jkt 211001
Before further flight after the replacement required by paragraph (e)(1) of this AD.
14 CFR Part 39
[Docket No. FAA–2007–28115; Directorate
Identifier 2007–CE–045–AD]
RIN 2120–AA64
considered as potentially hazardous/
catastrophic. This AD mandates additional
inspections considered necessary to address
the identified unsafe condition.
Note: The cause of this cracking is not
related to previous cracking of the radius rod
cylinder addressed by BAE Systems SB 32–
JA040945 (CAA AD G–2005–0010), however,
the consequences of a failure are the same.
Airworthiness Directives; British
Aerospace Regional Aircraft Model
HP.137 Jetstream Mk.1, Jetstream
Series 200, Jetstream Series 3101, and
Jetstream Model 3201 Airplanes
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
ADDRESSES:
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
There has been a report of landing gear
radius rods suffering cracks starting in the
flashline near the microswitch boss. Such
cracks can result in loss of the normal
hydraulic system and may lead to a landing
gear collapse. Main landing gear collapse is
PO 00000
Frm 00015
Fmt 4702
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We must receive comments on
this proposed AD by August 6, 2007.
DATES:
You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket 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.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
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Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov; or in
person at the Docket Management
Facility between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
proposed AD, the regulatory evaluation,
any comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4138; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–28115; Directorate Identifier
2007–CE–045–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
rmajette on PROD1PC64 with PROPOSALS
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No: 2007–
0087, dated March 30, 2007 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
There has been a report of landing gear
radius rods suffering cracks starting in the
flashline near the microswitch boss. Such
cracks can result in loss of the normal
hydraulic system and may lead to a landing
gear collapse. Main landing gear collapse is
considered as potentially hazardous/
catastrophic. This AD mandates additional
inspections considered necessary to address
the identified unsafe condition.
VerDate Aug<31>2005
15:25 Jul 05, 2007
Jkt 211001
Note: The cause of this cracking is not
related to previous cracking of the radius rod
cylinder addressed by BAE Systems SB 32–
JA040945 (CAA AD G–2005–0010), however,
the consequences of a failure are the same.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
British Aerospace Regional Aircraft
has issued British Aerospace Jetstream
Series 3100 and 3200 Service Bulletin
32–JA060741, dated November 1, 2006.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of the Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This Proposed AD
and the MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have proposed
different actions in this AD from those
in the MCAI in order to follow FAA
policies. Any such differences are
highlighted in a Note within the
proposed AD.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 190 products of U.S.
registry. We also estimate that it would
take about 14 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $80 per work-hour. Parts would
cost approximately $10,000 per product.
Based on these figures, we estimate the
cost of the proposed AD on U.S.
operators to be $2,112,800, or $11,120
per product.
PO 00000
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36915
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
E:\FR\FM\06JYP1.SGM
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36916
§ 39.13
Federal Register / Vol. 72, No. 129 / Friday, July 6, 2007 / Proposed Rules
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
British Aerospace Regional Aircraft: Docket
No. FAA–2007–28115; Directorate
Identifier 2007–CE–045–AD.
Comments Due Date
(a) We must receive comments by August
6, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to HP.137 Jetstream
Mk. 1, Jetstream Series 200, Jetstream Series
3101, and Jetstream Model 3201 airplanes, all
serial numbers, certificated in any category.
(d) Air Transport Association of America
(ATA) Code 32: Landing Gear.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
There has been a report of landing gear
radius rods suffering cracks starting in the
flashline near the microswitch boss. Such
cracks can result in loss of the normal
hydraulic system and may lead to a landing
gear collapse. Main landing gear collapse is
considered as potentially hazardous/
catastrophic. This AD mandates additional
inspections considered necessary to address
the identified unsafe condition.
rmajette on PROD1PC64 with PROPOSALS
Note: The cause of this cracking is not
related to previous cracking of the radius rod
cylinder addressed by BAE Systems SB 32–
JA040945 (CAA AD G–2005–0010), however,
the consequences of a failure are the same.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Initially within the next 3 months after
the effective date of this AD and repetitively
thereafter at intervals not to exceed 12
months until the replacement required by
paragraph (f)(2) or (f)(3) of this AD is done,
inspect the main landing gear radius rod
forged cylinder flashline following the
accomplishment instructions of British
Aerospace Jetstream Series 3100 and 3200
Service Bulletin 32–JA060741, dated
November 1, 2006.
(2) If cracks are found during any
inspection required by this AD, before further
flight, replace the radius rod assembly with
a serviceable unit.
(i) If the radius rod assembly includes the
parts described in paragraphs (f)(3)(i) and
(f)(3)(ii) of this AD, then the repetitive
inspections of this AD are no longer required.
(ii) If the radius rod assembly does not
include the parts described in paragraphs
(f)(3)(i) and (f)(3)(ii) of this AD, then continue
to repetitively inspect at intervals not to
exceed 12 months until you comply with
paragraph (f)(3) of this AD.
(3) Upon accumulating 8,000 total landings
TIS on the airplane or within the next 100
hours TIS after the effective date of this AD,
whichever occurs later, replace the radius
rod assembly by installing the following (this
terminates the repetitive inspection
requirement of this AD):
VerDate Aug<31>2005
15:25 Jul 05, 2007
Jkt 211001
(i) Part number (P/N) 1847/A to 1847/L
with strike-off 12 or 13, or 1847/M or later;
and
(ii) P/N 1862/A to 1862/L with strike-off 12
or 13, or 1862/M or later.
(4) For airplanes under 8,000 total
landings: Before further flight after the initial
inspection required by paragraph (f)(1) of this
AD, do not install a radius rod assembly that
is not of a part specified in paragraphs
(f)(3)(i) and (f)(3)(ii) of this AD on an affected
airplane, unless it has been inspected in
accordance with the requirements of this
directive.
(5) For airplanes that have replaced or
have the radius rod assembly replaced as
required in paragraph (f)(3) of this AD:
Before further flight after installing the parts
in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD,
do not install any radius rod assembly that
is not part number (P/N) 1847/A to 1847/L
with strike-off 12 or 13, or 1847/M or later;
and P/N 1862/A to 1862/L with strike-off 12
or 13, or 1862/M or later.
Note 1: When a compliance time in this AD
is presented in landings and you do not keep
the total landings, you may multiply the total
number of airplane hours TIS by 0.75 to
calculate the number of landings for the
purposes of doing the actions required by
this AD.
Note 2: Maintenance procedures for each
radius rod overhaul are included in APPH
Service Bulletin 1847–32–12 or 1862–32–12,
both dated September 2006, as applicable.
You may still perform such maintenance
through a fluorescent dye penetrant
inspection of the cylinder counterbore as
specified in APPH Component Maintenance
Manual (CMM) 32–10–16 at Revision 11 or
higher.
FAA AD Differences
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
Frm 00017
Fmt 4702
Related Information
(h) Refer to European Aviation Safety
Agency (EASA) AD No. 2007–0087, dated
March 30, 2007; and BAE SYSTEMS
Jetstream Series 3100 and 3200 Service
Bulletin 32–JA060741, dated November 1,
2006; for related information.
Issued in Kansas City, Missouri, on June
29, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–13091 Filed 7–5–07; 8:45 am]
BILLING CODE 4910–13–P
Note 3: This AD differs from the MCAI
and/or service information as follows:
(1) The MCAI and service bulletin allow
the radius rod assembly to be repetitively
inspected for the life of the airplane and the
repetitive inspections terminated if improved
design parts are installed. The affected
airplanes are used in commuter operations
(14 CFR part 135). The FAA’s policy on aging
commuter class aircraft states, when a
modification exists that could eliminate or
reduce the number of required critical
inspections, the modification should be
incorporated. Therefore, the FAA is
mandating the replacement of the radius rod
assembly with improved design parts no later
than upon accumulating 8,000 landings on
the airplane as terminating action for the
repetitive inspections.
(2) The MCAI includes procedures for a
maintenance overhaul referencing APPH
service bulletins. Because we do not require
general maintenance in our ADs, we added
a note referencing these bulletins.
PO 00000
found in 14 CFR 39.19. Send information to
ATTN: Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4138; fax: (816) 329–
4090. 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
(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.
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27811; Directorate
Identifier 2004–NE–11–AD]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Tay 611–8, Tay 611–8C,
Tay 620–15, Tay 650–15, and Tay 651–
54 Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) for Rolls-Royce
Deutschland (RRD) Tay 611–8, Tay 620–
15, Tay 650–15, and Tay 651–54
turbofan engines. That AD currently
requires initial and repetitive visual
E:\FR\FM\06JYP1.SGM
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]]>Agencies
[Federal Register Volume 72, Number 129 (Friday, July 6, 2007)]
[Proposed Rules]
[Pages 36914-36916]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13091]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28115; Directorate Identifier 2007-CE-045-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Regional Aircraft
Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series
3101, and Jetstream Model 3201 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
There has been a report of landing gear radius rods suffering
cracks starting in the flashline near the microswitch boss. Such
cracks can result in loss of the normal hydraulic system and may
lead to a landing gear collapse. Main landing gear collapse is
considered as potentially hazardous/catastrophic. This AD mandates
additional inspections considered necessary to address the
identified unsafe condition.
Note: The cause of this cracking is not related to previous
cracking of the radius rod cylinder addressed by BAE Systems SB 32-
JA040945 (CAA AD G-2005-0010), however, the consequences of a
failure are the same.
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by August 6, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: Docket 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.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
[[Page 36915]]
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov; or in person at the Docket Management Facility between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this proposed AD, the regulatory evaluation, any
comments received, and other information. The street address for the
Docket Office (telephone (800) 647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4138; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28115; Directorate Identifier 2007-CE-045-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued AD
No: 2007-0087, dated March 30, 2007 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
There has been a report of landing gear radius rods suffering
cracks starting in the flashline near the microswitch boss. Such
cracks can result in loss of the normal hydraulic system and may
lead to a landing gear collapse. Main landing gear collapse is
considered as potentially hazardous/catastrophic. This AD mandates
additional inspections considered necessary to address the
identified unsafe condition.
Note: The cause of this cracking is not related to previous
cracking of the radius rod cylinder addressed by BAE Systems SB 32-
JA040945 (CAA AD G-2005-0010), however, the consequences of a
failure are the same.
You may obtain further information by examining the MCAI in the
AD docket.
Relevant Service Information
British Aerospace Regional Aircraft has issued British Aerospace
Jetstream Series 3100 and 3200 Service Bulletin 32-JA060741, dated
November 1, 2006. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of the Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed AD and the MCAI or Service
Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 190 products of U.S. registry. We also estimate that
it would take about 14 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Parts would cost approximately $10,000 per product. Based on
these figures, we estimate the cost of the proposed AD on U.S.
operators to be $2,112,800, or $11,120 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 36916]]
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
British Aerospace Regional Aircraft: Docket No. FAA-2007-28115;
Directorate Identifier 2007-CE-045-AD.
Comments Due Date
(a) We must receive comments by August 6, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to HP.137 Jetstream Mk. 1, Jetstream Series
200, Jetstream Series 3101, and Jetstream Model 3201 airplanes, all
serial numbers, certificated in any category.
(d) Air Transport Association of America (ATA) Code 32: Landing
Gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
There has been a report of landing gear radius rods suffering
cracks starting in the flashline near the microswitch boss. Such
cracks can result in loss of the normal hydraulic system and may
lead to a landing gear collapse. Main landing gear collapse is
considered as potentially hazardous/catastrophic. This AD mandates
additional inspections considered necessary to address the
identified unsafe condition.
Note: The cause of this cracking is not related to previous
cracking of the radius rod cylinder addressed by BAE Systems SB 32-
JA040945 (CAA AD G-2005-0010), however, the consequences of a
failure are the same.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) Initially within the next 3 months after the effective date
of this AD and repetitively thereafter at intervals not to exceed 12
months until the replacement required by paragraph (f)(2) or (f)(3)
of this AD is done, inspect the main landing gear radius rod forged
cylinder flashline following the accomplishment instructions of
British Aerospace Jetstream Series 3100 and 3200 Service Bulletin
32-JA060741, dated November 1, 2006.
(2) If cracks are found during any inspection required by this
AD, before further flight, replace the radius rod assembly with a
serviceable unit.
(i) If the radius rod assembly includes the parts described in
paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, then the repetitive
inspections of this AD are no longer required.
(ii) If the radius rod assembly does not include the parts
described in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, then
continue to repetitively inspect at intervals not to exceed 12
months until you comply with paragraph (f)(3) of this AD.
(3) Upon accumulating 8,000 total landings TIS on the airplane
or within the next 100 hours TIS after the effective date of this
AD, whichever occurs later, replace the radius rod assembly by
installing the following (this terminates the repetitive inspection
requirement of this AD):
(i) Part number (P/N) 1847/A to 1847/L with strike-off 12 or 13,
or 1847/M or later; and
(ii) P/N 1862/A to 1862/L with strike-off 12 or 13, or 1862/M or
later.
(4) For airplanes under 8,000 total landings: Before further
flight after the initial inspection required by paragraph (f)(1) of
this AD, do not install a radius rod assembly that is not of a part
specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD on an
affected airplane, unless it has been inspected in accordance with
the requirements of this directive.
(5) For airplanes that have replaced or have the radius rod
assembly replaced as required in paragraph (f)(3) of this AD: Before
further flight after installing the parts in paragraphs (f)(3)(i)
and (f)(3)(ii) of this AD, do not install any radius rod assembly
that is not part number (P/N) 1847/A to 1847/L with strike-off 12 or
13, or 1847/M or later; and P/N 1862/A to 1862/L with strike-off 12
or 13, or 1862/M or later.
Note 1: When a compliance time in this AD is presented in
landings and you do not keep the total landings, you may multiply
the total number of airplane hours TIS by 0.75 to calculate the
number of landings for the purposes of doing the actions required by
this AD.
Note 2: Maintenance procedures for each radius rod overhaul are
included in APPH Service Bulletin 1847-32-12 or 1862-32-12, both
dated September 2006, as applicable. You may still perform such
maintenance through a fluorescent dye penetrant inspection of the
cylinder counterbore as specified in APPH Component Maintenance
Manual (CMM) 32-10-16 at Revision 11 or higher.
FAA AD Differences
Note 3: This AD differs from the MCAI and/or service information
as follows:
(1) The MCAI and service bulletin allow the radius rod assembly
to be repetitively inspected for the life of the airplane and the
repetitive inspections terminated if improved design parts are
installed. The affected airplanes are used in commuter operations
(14 CFR part 135). The FAA's policy on aging commuter class aircraft
states, when a modification exists that could eliminate or reduce
the number of required critical inspections, the modification should
be incorporated. Therefore, the FAA is mandating the replacement of
the radius rod assembly with improved design parts no later than
upon accumulating 8,000 landings on the airplane as terminating
action for the repetitive inspections.
(2) The MCAI includes procedures for a maintenance overhaul
referencing APPH service bulletins. Because we do not require
general maintenance in our ADs, we added a note referencing these
bulletins.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Staff, 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: Taylor Martin, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4138; fax: (816) 329-4090. 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 (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 European Aviation Safety Agency (EASA) AD No. 2007-
0087, dated March 30, 2007; and BAE SYSTEMS Jetstream Series 3100
and 3200 Service Bulletin 32-JA060741, dated November 1, 2006; for
related information.
Issued in Kansas City, Missouri, on June 29, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E7-13091 Filed 7-5-07; 8:45 am]
BILLING CODE 4910-13-P
