[Federal Register: July 6, 2007 (Volume 72, Number 129)]
[Proposed Rules]
[Page 36914-36916]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06jy07-22]
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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).
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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 http://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 http://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 http://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