Airworthiness Directives; British Aerospace Regional Aircraft Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 Airplanes, 60228-60231 [E7-20364]
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Federal Register / Vol. 72, No. 205 / Wednesday, October 24, 2007 / Rules and Regulations
(2) Is not a ‘‘significant rule’’ under
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 summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
Interim Action
(f) These actions are interim actions due to
the on-going investigation, and we may take
further rulemaking actions in the future
based on the results of the investigation and
field experience.
Alternative Methods of Compliance
(l) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Engine Electronic Control Unit (ECU)
Software Removal
(g) At the next shop visit of the engine or
of the ECU, whichever occurs first, and not
to exceed 60 months from the effective date
of this AD, remove the following software
versions from the ECUs:
Special Flight Permits
(m) Special flight permits are not
authorized.
TABLE 1.—REMOVAL OF ECU
SOFTWARE VERSIONS
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
Software
version
Installed in ECU Part No.
(1) 8.5.A ...
Adoption of the Amendment
1851M51P01,
1851M51P02,
1851M52P01, 1851M52P02,
1851M53P01, 1851M53P02
1471M69P01,
1471M69P02,
1519M91P01
1519M91P02
1519M91P03, 1519M91P04
1519M91P05
1519M91P06, 1820M34P01
1519M91P07, 1820M34P02
1519M91P09,
1519M91P10,
1820M34P04, 1820M34P05
(2) 8.3C ...
(3)
(4)
(5)
(6)
(7)
(8)
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
8.3.D ..
8.3.E ...
8.3.F ...
8.3.G ..
8.3.H ..
8.3.J ...
Related Information
(n) Information on removing ECU software
and installing new software, which provides
increased margin to flameout, can be found
in GE Service Bulletin No. CF6–80C2 S/B 73–
0351, dated April 11, 2007.
(o) Contact John Golinski, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: john.golinski@faa.gov;
telephone: (781) 238–7135, fax: (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
October 17, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–20813 Filed 10–23–07; 8:45 am]
BILLING CODE 4910–13–P
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2007–22–07 General Electric Company:
Amendment 39–15243. Docket No.
FAA–2007–28319; Directorate Identifier
2007–NE–27–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective November 28, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric
Company (GE) CF6–80C2D1F turbofan
engines, installed on, but not limited to,
McDonnell Douglas Corporation MD–11
series airplanes.
yshivers on PROD1PC62 with RULES
Unsafe Condition
(d) This AD results from reports of engine
flameout events during flight, including
reports of events where all engines
simultaneously experienced a flameout or
other adverse operation. We are issuing this
AD to minimize engine flameout due to ice
accretion and shedding during flight.
Exposure to ice crystals during flight is
believed to be associated with these flameout
events.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
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Previous Software Versions of ECU Software
(h) For a period of 24 months after the
effective date of this AD, once an ECU
containing a software version not listed in
Table 1 of this AD is installed on an engine,
that ECU can be replaced with an ECU
containing a previous version of software
listed in Table 1.
(i) Once the software version listed in
Table 1 of this AD has been removed and
new FAA-approved software version is
installed in an ECU, reverting to those older
software versions in that ECU is prohibited.
(j) After 60 months from the effective date
of this AD, use of an ECU with a software
version listed in Table 1 of this AD is
prohibited.
DEPARTMENT OF TRANSPORTATION
Definitions
(k) For the purposes of this AD:
(1) Next shop visit of the ECU is when the
ECU is removed from the engine for overhaul
or maintenance after the effective date of this
AD.
(2) Next shop visit of the engine is when
the engine is removed from the airplane for
maintenance in which a major flange is
disassembled after the effective date of this
AD. The following engine maintenance
actions, either separately or in combination
with each other, are not considered a next
shop visit of the engine:
(i) Removal of the upper high pressure
compressor (HPC) stator case solely for airfoil
maintenance.
(ii) Module-level inspection of the HPC
rotor stages 3–9 spool.
(iii) Replacement of stage 5 HPC variable
stator vane bushings or lever arms.
(iv) Removal of the accessory gearbox.
(v) Replacement of the inlet gearbox
polytetrafluoroethylene seal.
AGENCY:
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28115 Directorate
Identifier 2007–CE–045–AD; Amendment
39–15235; AD 2007–21–17]
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
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)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
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/
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Federal Register / Vol. 72, No. 205 / Wednesday, October 24, 2007 / Rules and Regulations
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.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
November 28, 2007.
On November 28, 2007, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
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:
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 July 6, 2007 (72 FR 36914).
That NPRM proposed 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.
yshivers on PROD1PC62 with RULES
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received.
Comment Issue: Compliance Time
APPH, the original equipment
manufacturer of the main landing gear
of the affected airplanes, expresses
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15:22 Oct 23, 2007
Jkt 214001
concern over being able to supply the
necessary parts for the mandatory
replacement. APPH understands the
FAA’s policy on aging commuter class
aircraft, but states that all airplanes will
have accumulated 8,000 total landings.
Therefore, the proposed AD would
require the replacement on all airplanes
within 100 hours time-in-service (TIS)
after the effective date of the AD. APPH
recommends a compliance time of ‘‘at
the next scheduled overhaul.’’
The FAA partially concurs. We
understand the problem with supplying
parts for all airplanes within 100 hours
TIS. However, the airplanes may not
have ‘‘scheduled overhauls,’’ since the
overhaul program is a recommended
overhaul program and not a mandatory
overhaul program. The FAA has
determined that changing the 100-hour
TIS grace period to 12 months would
eliminate the repetitive inspections and
provide additional time for operators to
acquire the needed parts.
We are changing the mandatory
replacement compliance time in the
final rule AD action to read ‘‘upon
reaching 8,000 total landings on the
main landing gear radius rods or within
the next 12 months after the effective
date of this AD, whichever occurs
later.’’
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required 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 AD.
Costs of Compliance
We estimate that this AD will affect
190 products of U.S. registry. We also
estimate that it will take about 14 workhours per product to comply with basic
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60229
requirements of this AD. The average
labor rate is $80 per work-hour.
Required parts will cost about $10,000
per product.
Based on these figures, we estimate
the cost of this AD to the 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 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
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 Management Facility 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
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60230
Federal Register / Vol. 72, No. 205 / Wednesday, October 24, 2007 / Rules and Regulations
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2007–21–17 British Aerospace Regional
Aircraft: Amendment 39–15235; Docket
No. FAA–2007–28115; Directorate
Identifier 2007–CE–045–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective November 28, 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.
yshivers on PROD1PC62 with RULES
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
November 28, 2007 (the effective date of this
AD) and repetitively thereafter at intervals
not to exceed 12 months until the
VerDate Aug<31>2005
15:22 Oct 23, 2007
Jkt 214001
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 reaching 8,000 total landings on
the main landing gear radius rods or within
the next 12 months November 28, 2007(the
effective date of this AD), whichever occurs
later, replace the radius rod assembly by
installing one of the following part numbers
(P/N). This terminates the repetitive
inspection requirement of this AD:
(i) 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
on the main landing gear radius rods: 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
one of the parts 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 paragraph (f)(1) of this AD.
(5) For those airplanes with parts listed 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 does not
incorporate the parts in paragraphs (f)(3)(i)
and (f)(3)(ii) of this AD.
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 time-in-service 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 do such maintenance using the
above referenced bulletins or 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 inspection requirement is
terminated if improved design parts are
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installed. Many of the affected airplanes are
used in commuter operations (14 CFR part
135). The FAA’s policy on aging commuter
class aircraft states that 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 reaching
8,000 total landings on the main landing gear
radius rods or within the next 12 months
after the effective date of this AD, whichever
occurs later.
(2) The MCAI includes a reference to APPH
service bulletins as an option for
maintenance overhaul procedures. Because
we do not require general maintenance in our
ADs, we added a note referencing these
bulletins as an option to use for overhaul
procedures.
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 FAAapproved 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.
Material Incorporated by Reference
(i) You must use BAE SYSTEMS Jetstream
Series 3100 and 3200 Service Bulletin 32–
JA060741, dated November 1, 2006 to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
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Federal Register / Vol. 72, No. 205 / Wednesday, October 24, 2007 / Rules and Regulations
(2) For service information identified in
this AD, contact British Aerospace
(Operations) Limited Trading at British
Aerospace Regional Aircraft, Prestwick
International Airport, Ayrshire KA9 2RW,
Scotland.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on
October 10, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–20364 Filed 10–23–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28923; Directorate
Identifier 2007–NM–133–AD; Amendment
39–15242; AD 2007–22–06]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 0070 and 0100
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
yshivers on PROD1PC62 with RULES
SUMMARY:
Over the years, several Fokker 100 (F28
Mark 0100) operators reported that a MLG
(main landing gear) wheel fell off during
regular operation of the aircraft. These
incidents occurred due to a missing spacer,
which had inadvertently not been installed
during a previous wheel change. Omitting
the installation of the wheel spacer allows
the wheel to move sideways along the axle,
which subsequently leads to bearing failure,
followed by loss of the wheel. * * * This
condition, if not corrected, * * * could
conceivably result in loss of control of the
aircraft during the take-off run, landing
rollout or taxiing operations. * * *
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
VerDate Aug<31>2005
15:22 Oct 23, 2007
Jkt 214001
This AD becomes effective
November 28, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 28, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.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.
DATES:
FOR FURTHER INFORMATION CONTACT:
Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1137; 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 August 16, 2007 (72 FR
45956). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
Over the years, several Fokker 100 (F28
Mark 0100) operators reported that a MLG
(main landing gear) wheel fell off during
regular operation of the aircraft. These
incidents occurred due to a missing spacer,
which had inadvertently not been installed
during a previous wheel change. Omitting
the installation of the wheel spacer allows
the wheel to move sideways along the axle,
which subsequently leads to bearing failure,
followed by loss of the wheel. Investigation
by Fokker and Messier-Dowty has shown that
two separate items, the spacer and the axle
nut, can be replaced by a single axle-nut/
spacer assembly, to prevent the possibility of
omitting the spacer. In 1995, Messier-Dowty
issued Service Bulletin (SB) F100–32–72 to
make sure that the operator does not
assemble the axle nut without the spacer.
Fokker subsequently issued SB F100–32–096
to notify Fokker 100 operators of the
(optional) Messier-Dowty SB’s existence. At
a later stage, Fokker revised the SB to the
status of ‘‘recommended’’. In spite of all this
attention to the spacer problem, wheel losses
are still being reported due to missing wheel
nut spacers. This condition, if not corrected,
may lead to further wheel loss incidents,
each of which could conceivably result in
loss of control of the aircraft during the takeoff run, landing rollout or taxiing operations.
Since a potentially unsafe condition has been
identified that may exist or develop on
aircraft of the same type design, this
Airworthiness Directive requires the
replacement of the axle-nut and spacer with
an integrated axle-nut/spacer assembly. In
addition, the Aircraft Maintenance Manual
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Sfmt 4700
60231
(AMM) and Illustrated Parts Catalogue (IPC)
must be amended to prevent reversal to a
separate axle-nut and spacer installation
during a subsequent wheel change.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect
13 products of U.S. registry. We also
estimate that it will take about 4 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
Required parts will cost about $3,750
per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that there will be no
charge for these parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of
this AD to the U.S. operators to be
$52,910, or $4,070 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.
E:\FR\FM\24OCR1.SGM
24OCR1
]]>Agencies
[Federal Register Volume 72, Number 205 (Wednesday, October 24, 2007)]
[Rules and Regulations]
[Pages 60228-60231]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-20364]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28115 Directorate Identifier 2007-CE-045-AD;
Amendment 39-15235; AD 2007-21-17]
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: 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) issued by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
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/
[[Page 60229]]
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.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective November 28, 2007.
On November 28, 2007, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in this
AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
www.regulations.gov or in person at Document Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: 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:
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 July 6, 2007 (72 FR
36914). That NPRM proposed 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.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received.
Comment Issue: Compliance Time
APPH, the original equipment manufacturer of the main landing gear
of the affected airplanes, expresses concern over being able to supply
the necessary parts for the mandatory replacement. APPH understands the
FAA's policy on aging commuter class aircraft, but states that all
airplanes will have accumulated 8,000 total landings. Therefore, the
proposed AD would require the replacement on all airplanes within 100
hours time-in-service (TIS) after the effective date of the AD. APPH
recommends a compliance time of ``at the next scheduled overhaul.''
The FAA partially concurs. We understand the problem with supplying
parts for all airplanes within 100 hours TIS. However, the airplanes
may not have ``scheduled overhauls,'' since the overhaul program is a
recommended overhaul program and not a mandatory overhaul program. The
FAA has determined that changing the 100-hour TIS grace period to 12
months would eliminate the repetitive inspections and provide
additional time for operators to acquire the needed parts.
We are changing the mandatory replacement compliance time in the
final rule AD action to read ``upon reaching 8,000 total landings on
the main landing gear radius rods or within the next 12 months after
the effective date of this AD, whichever occurs later.''
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required 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 AD.
Costs of Compliance
We estimate that this AD will affect 190 products of U.S. registry.
We also estimate that it will take about 14 work-hours per product to
comply with basic requirements of this AD. The average labor rate is
$80 per work-hour. Required parts will cost about $10,000 per product.
Based on these figures, we estimate the cost of this AD to the 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 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 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 Management Facility
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
[[Page 60230]]
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.
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:
2007-21-17 British Aerospace Regional Aircraft: Amendment 39-15235;
Docket No. FAA-2007-28115; Directorate Identifier 2007-CE-045-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
28, 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 November 28, 2007
(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 reaching 8,000 total landings on the main landing gear
radius rods or within the next 12 months November 28, 2007(the
effective date of this AD), whichever occurs later, replace the
radius rod assembly by installing one of the following part numbers
(P/N). This terminates the repetitive inspection requirement of this
AD:
(i) 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 on the main landing
gear radius rods: 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 one of the parts 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 paragraph (f)(1) of this
AD.
(5) For those airplanes with parts listed 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 does not incorporate the parts in
paragraphs (f)(3)(i) and (f)(3)(ii) of this AD.
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 time-in-service 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 do such maintenance
using the above referenced bulletins or 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 inspection requirement is terminated if improved design
parts are installed. Many of the affected airplanes are used in
commuter operations (14 CFR part 135). The FAA's policy on aging
commuter class aircraft states that 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 reaching 8,000 total landings on
the main landing gear radius rods or within the next 12 months after
the effective date of this AD, whichever occurs later.
(2) The MCAI includes a reference to APPH service bulletins as
an option for maintenance overhaul procedures. Because we do not
require general maintenance in our ADs, we added a note referencing
these bulletins as an option to use for overhaul procedures.
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.
Material Incorporated by Reference
(i) You must use BAE SYSTEMS Jetstream Series 3100 and 3200
Service Bulletin 32-JA060741, dated November 1, 2006 to do the
actions required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
[[Page 60231]]
(2) For service information identified in this AD, contact
British Aerospace (Operations) Limited Trading at British Aerospace
Regional Aircraft, Prestwick International Airport, Ayrshire KA9
2RW, Scotland.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on October 10, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-20364 Filed 10-23-07; 8:45 am]
BILLING CODE 4910-13-P
