Airworthiness Directives; Cessna Aircraft Company Models 208 and 208B Airplanes, 34216-34218 [E9-16465]
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34216
Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0638; Directorate
Identifier 2009–CE–038–AD; Amendment
39–15968; AD 2009–15–05]
RIN 2120–AA64
Airworthiness Directives; Cessna
Aircraft Company Models 208 and
208B Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
srobinson on DSKHWCL6B1PROD with RULES
SUPPLEMENTARY INFORMATION:
Discussion
We are adopting a new
airworthiness directive (AD) for certain
Cessna Aircraft Company (Cessna)
Models 208 and 208B airplanes. This
AD requires you to measure the roll and
the yaw bridle cable tension (adjusting
as necessary) and to torque the clamp
screws. This AD results from two
reported incidences of slack bridle
cables with the swaged balls unseating
from their drum recesses. We are issuing
this AD to detect and correct loose
bridle cable clamps, which could result
in the swaged ball unseating from the
recess in the servo drum and contacting
the cable guard pin. This failure could
lead to very limited control of the
rudder and/or aileron with consequent
loss of control.
DATES: This AD becomes effective on
July 27, 2009.
On July 27, 2009, the Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
We must receive any comments on
this AD by September 14, 2009.
ADDRESSES: Use one of the following
addresses to comment on this AD.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: 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.
To get the service information
identified in this AD, contact Cessna
Aircraft Company, Product Support,
P.O. Box 7706; Wichita, Kansas 67277;
SUMMARY:
VerDate Nov<24>2008
15:15 Jul 14, 2009
Jkt 217001
telephone: (316) 517–5800; fax: (316)
942–9006; Internet: https://
www.cessna.com.
To view the comments to this AD, go
to https://www.regulations.gov. The
docket number is FAA–2009–0638;
Directorate Identifier 2009–CE–038–AD.
FOR FURTHER INFORMATION CONTACT: Ann
Johnson, Aerospace Engineer, Wichita
Aircraft Certification Office (ACO), 1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4105; fax: (316) 946–4107; E-mail:
ann.johnson@faa.gov.
We received reports on two Cessna
Models 208 and 208B production
airplanes with autopilot heading
squawks. Upon investigation by the
manufacturer, technicians found in both
cases the bridle cable for the autopilot
aileron servo was slack, and the swaged
ball was unseated from the drum recess.
The cause of the bridle cables going
slack was insufficient torque on the
bridle cable clamp screws, allowing
slippage of the bridle cable clamps on
the roll bridle cable. Since the rudder
and aileron autopilot interface are
similar, the same condition could exist
with the yaw bridle cable.
This condition, if not corrected, could
result in the swaged ball unseating from
the recess in the servo drum and
contacting the cable guard pin. This
failure could lead to very limited
control of the rudder and/or aileron
with consequent loss of control.
Relevant Service Information
We reviewed Cessna Aircraft
Company Caravan Service Bulletin
CAB08–9, dated November 24, 2008.
The service information describes
procedures for inspecting the bridle
cables for looseness, adjusting the bridle
cable tension, and tightening the bridle
cable clamp screws to the correct
torque. The manufacturer intends that
the actions specified in the service
information adequately address the
unsafe condition.
FAA’s Determination and Requirements
of This AD
We are issuing this AD because we
evaluated all the information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This AD requires you to
measure the autopilot roll and yaw
bridle cable tensions (adjusting as
necessary) and to torque the bridle cable
clamp screws.
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because the swaged ball on the
bridle cable could unseat from the servo
drum and contact the cable guard pin.
This failure could lead to very limited
control of the rudder and/or aileron.
Therefore, we determined that notice
and opportunity for public comment
before issuing this AD are impracticable
and that good cause exists for making
this amendment effective in fewer than
30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and an
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments regarding this
AD. Send your comments to an address
listed under the ADDRESSES section.
Include the docket number ‘‘FAA–
2009–0638; Directorate Identifier 2009–
CE–038–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD. We will consider all
comments received by the closing date
and may amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
concerning this AD.
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
E:\FR\FM\15JYR1.SGM
15JYR1
Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations
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 that 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 that
contains the AD, the regulatory
evaluation, any comments received, and
other information 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 Docket Office (telephone (800) 647–
5527) is located at the street address
stated 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.
Effective Date
(a) This AD becomes effective on July 27,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
airplane models and serial numbers that are
certificated in any category:
Model
Serial No.
208 ......
208B ....
Adoption of the Amendment
20800500 through 20800504.
208B1216, 208B2001, 208B2003
through 208B2023, 208B2025
through 208B2029, 208B2031
through 208B2037, 208B2040,
208B2042, and 208B2043.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
Unsafe Condition
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
34217
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
2009–15–05 Cessna Aircraft Company:
Amendment 39–15968; Docket No.
FAA–2009–0638; Directorate Identifier
2009–CE–038–AD.
(d) This AD is the result of two reported
incidences of slack bridle cables with the
swaged balls unseated from their drum
recesses. We are issuing this AD to detect and
correct loose bridle cable clamps, which
could result in the swaged ball unseating
from the recess in the servo drum and
contacting the cable guard pin. This failure
could lead to very limited control of the
rudder and/or aileron with consequent loss
of control.
Compliance
(e) To address this problem, you must do
the following, unless already done:
Actions
Compliance
Procedures
(1) Measure and adjust as necessary, the roll
bridle cable tension and yaw bridle cable tension, and torque the 12 bridle cable clamp
screws.
(2) Use the form (Figure 1 of this AD) to report
the results of the inspections required in
paragraph (e)(1) of this AD. The Office of
Management and Budget (OMB) approved
the information collection requirements contained in this regulation under the provisions
of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.) and assigned OMB
Control Number 2120–0056.
Within the next 10 hours time-in-service after
July 27, 2009 (the effective date of this AD).
Follow Accomplishment Instructions, paragraphs 2. through 7., of Cessna Aircraft
Company Caravan Service Bulletin CAB08–
9, dated November 24, 2008.
Send the report to the FAA at the address
specified in paragraph (f) of this AD.
Within 10 days after the inspection required in
paragraph (e)(1). If Cessna Aircraft Company Caravan Service Bulletin CAB08–9,
dated November 24, 2008, was done before July 27, 2009 (the effective date of this
AD) the report is not required.
AD 2009–15–05 INSPECTION REPORT
[If the SB was done before the effective date of this AD, this report does not need to be completed and returned to the Wichita ACO]
Airplane Model
Airplane Serial Number
srobinson on DSKHWCL6B1PROD with RULES
Did you find the yaw bridle
cable tension to be within
the range of 15–25 lbs?
Did you find the roll bridle
cable tension to be within
the range of 10–14 lbs?
Were any other discrepancies noted during the
inspection?
VerDate Nov<24>2008
15:15 Jul 14, 2009
Jkt 217001
PO 00000
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Fmt 4700
Sfmt 4700
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15JYR1
34218
Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations
AD 2009–15–05 INSPECTION REPORT—Continued
[If the SB was done before the effective date of this AD, this report does not need to be completed and returned to the Wichita ACO]
Name
Telephone and/or e-mail address
Date
Send report to:
Ann Johnson, Aerospace Engineer
ACE–116W, Wichita Aircraft Certification Office
1801 Airport Road, Room 100
Wichita, KS 67209
fax: (316) 946–4107
e-mail: ann.johnson@faa.gov
Figure 1
Alternative Methods of Compliance
(AMOCs)
(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: Ann
Johnson, Aerospace Engineer, Wichita
Aircraft Certification Office (ACO), 1801
Airport Road, Room 100, Wichita, Kansas
67209; telephone: (316) 946–4105; fax: (316)
946–4107; E-mail: ann.johnson@faa.gov.
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.
srobinson on DSKHWCL6B1PROD with RULES
Material Incorporated by Reference
(g) You must use Cessna Aircraft Company
Caravan Service Bulletin CAB08–9, dated
November 24, 2008, to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Cessna Aircraft Company,
Product Support, P.O. Box 7706; Wichita,
Kansas 67277; telephone: (316) 517–5800;
fax: (316) 942–9006; Internet: https://
www.cessna.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
VerDate Nov<24>2008
15:15 Jul 14, 2009
Jkt 217001
Issued in Kansas City, Missouri, on July 6,
2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9–16465 Filed 7–14–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0832; Directorate
Identifier 2008–NM–067–AD; Amendment
39–15965; AD 2009–15–02]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
In-service experience has shown that a
fracture of the gerotor pump of the A320 RAT
[ram air turbine] may occur. This may lead
to the non-operation of the RAT in case of
an in-flight deployment.
The Non-Deployment or NonPressurization of the RAT, associated with a
double engine failure or a total loss of normal
electrical power generation constitutes an
unsafe condition.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
DATES: This AD becomes effective
August 19, 2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 19, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2141; 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 4, 2008 (73 FR
45174). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
In-service experience has shown that a
fracture of the gerotor pump of the A320 RAT
[ram air turbine] may occur. This may lead
to the non-operation of the RAT in case of
an in-flight deployment.
The Non-Deployment or NonPressurization of the RAT, associated with a
double engine failure or a total loss of normal
electrical power generation constitutes an
unsafe condition.
This AD mandates the replacement of the
affected gerotor pump assembly, which will
provide the required improved reliability of
the RAT.
The implementation of this modification
was originally managed by an AIRBUS
monitoring campaign. However, the rate of
installation of the modification by operators
has not met the predicted target. As such and
E:\FR\FM\15JYR1.SGM
15JYR1
]]>Agencies
[Federal Register Volume 74, Number 134 (Wednesday, July 15, 2009)]
[Rules and Regulations]
[Pages 34216-34218]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-16465]
[[Page 34216]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0638; Directorate Identifier 2009-CE-038-AD;
Amendment 39-15968; AD 2009-15-05]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 208 and
208B Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD
requires you to measure the roll and the yaw bridle cable tension
(adjusting as necessary) and to torque the clamp screws. This AD
results from two reported incidences of slack bridle cables with the
swaged balls unseating from their drum recesses. We are issuing this AD
to detect and correct loose bridle cable clamps, which could result in
the swaged ball unseating from the recess in the servo drum and
contacting the cable guard pin. This failure could lead to very limited
control of the rudder and/or aileron with consequent loss of control.
DATES: This AD becomes effective on July 27, 2009.
On July 27, 2009, the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
We must receive any comments on this AD by September 14, 2009.
ADDRESSES: Use one of the following addresses to comment on this AD.
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: 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.
To get the service information identified in this AD, contact
Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita,
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006; Internet:
https://www.cessna.com.
To view the comments to this AD, go to https://www.regulations.gov.
The docket number is FAA-2009-0638; Directorate Identifier 2009-CE-038-
AD.
FOR FURTHER INFORMATION CONTACT: Ann Johnson, Aerospace Engineer,
Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room
100, Wichita, Kansas 67209; telephone: (316) 946-4105; fax: (316) 946-
4107; E-mail: ann.johnson@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We received reports on two Cessna Models 208 and 208B production
airplanes with autopilot heading squawks. Upon investigation by the
manufacturer, technicians found in both cases the bridle cable for the
autopilot aileron servo was slack, and the swaged ball was unseated
from the drum recess.
The cause of the bridle cables going slack was insufficient torque
on the bridle cable clamp screws, allowing slippage of the bridle cable
clamps on the roll bridle cable. Since the rudder and aileron autopilot
interface are similar, the same condition could exist with the yaw
bridle cable.
This condition, if not corrected, could result in the swaged ball
unseating from the recess in the servo drum and contacting the cable
guard pin. This failure could lead to very limited control of the
rudder and/or aileron with consequent loss of control.
Relevant Service Information
We reviewed Cessna Aircraft Company Caravan Service Bulletin CAB08-
9, dated November 24, 2008. The service information describes
procedures for inspecting the bridle cables for looseness, adjusting
the bridle cable tension, and tightening the bridle cable clamp screws
to the correct torque. The manufacturer intends that the actions
specified in the service information adequately address the unsafe
condition.
FAA's Determination and Requirements of This AD
We are issuing this AD because we evaluated all the information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design. This AD requires
you to measure the autopilot roll and yaw bridle cable tensions
(adjusting as necessary) and to torque the bridle cable clamp screws.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because the
swaged ball on the bridle cable could unseat from the servo drum and
contact the cable guard pin. This failure could lead to very limited
control of the rudder and/or aileron. Therefore, we determined that
notice and opportunity for public comment before issuing this AD are
impracticable and that good cause exists for making this amendment
effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and an opportunity for
public comment. We invite you to send any written relevant data, views,
or arguments regarding this AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number ``FAA-2009-0638;
Directorate Identifier 2009-CE-038-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive concerning this AD.
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
[[Page 34217]]
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 that 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 that contains the AD, the regulatory
evaluation, any comments received, and other information 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 Docket Office (telephone (800) 647-5527)
is located at the street address stated 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
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]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
2009-15-05 Cessna Aircraft Company: Amendment 39-15968; Docket No.
FAA-2009-0638; Directorate Identifier 2009-CE-038-AD.
Effective Date
(a) This AD becomes effective on July 27, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following airplane models and serial
numbers that are certificated in any category:
------------------------------------------------------------------------
Model Serial No.
------------------------------------------------------------------------
208.............................. 20800500 through 20800504.
208B............................. 208B1216, 208B2001, 208B2003 through
208B2023, 208B2025 through 208B2029,
208B2031 through 208B2037, 208B2040,
208B2042, and 208B2043.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD is the result of two reported incidences of slack
bridle cables with the swaged balls unseated from their drum
recesses. We are issuing this AD to detect and correct loose bridle
cable clamps, which could result in the swaged ball unseating from
the recess in the servo drum and contacting the cable guard pin.
This failure could lead to very limited control of the rudder and/or
aileron with consequent loss of control.
Compliance
(e) To address this problem, you must do the following, unless
already done:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Measure and adjust as Within the next 10 Follow
necessary, the roll bridle hours time-in- Accomplishment
cable tension and yaw service after July Instructions,
bridle cable tension, and 27, 2009 (the paragraphs 2.
torque the 12 bridle cable effective date of through 7., of
clamp screws. this AD). Cessna Aircraft
Company Caravan
Service Bulletin
CAB08-9, dated
November 24, 2008.
(2) Use the form (Figure 1 Within 10 days after Send the report to
of this AD) to report the the inspection the FAA at the
results of the inspections required in address specified
required in paragraph paragraph (e)(1). in paragraph (f) of
(e)(1) of this AD. The If Cessna Aircraft this AD.
Office of Management and Company Caravan
Budget (OMB) approved the Service Bulletin
information collection CAB08-9, dated
requirements contained in November 24, 2008,
this regulation under the was done before
provisions of the Paperwork July 27, 2009 (the
Reduction Act of 1980 (44 effective date of
U.S.C. 3501 et seq.) and this AD) the report
assigned OMB Control Number is not required.
2120-0056.
------------------------------------------------------------------------
AD 2009-15-05 Inspection Report
[If the SB was done before the effective date of this AD, this report
does not need to be completed and returned to the Wichita ACO]
------------------------------------------------------------------------
------------------------------------------------------------------------
Airplane Model ............................
------------------------------------------------------------------------
Airplane Serial Number ............................
------------------------------------------------------------------------
Did you find the yaw bridle cable tension ............................
to be within the range of 15-25 lbs?
------------------------------------------------------------------------
Did you find the roll bridle cable tension ............................
to be within the range of 10-14 lbs?
------------------------------------------------------------------------
Were any other discrepancies noted during ............................
the inspection?
------------------------------------------------------------------------
[[Page 34218]]
Name ............................
------------------------------------------------------------------------
Telephone and/or e-mail address ............................
------------------------------------------------------------------------
Date ............................
------------------------------------------------------------------------
Send report to:
Ann Johnson, Aerospace Engineer
ACE-116W, Wichita Aircraft Certification Office
1801 Airport Road, Room 100
Wichita, KS 67209
fax: (316) 946-4107
e-mail: ann.johnson@faa.gov
------------------------------------------------------------------------
Figure 1
Alternative Methods of Compliance (AMOCs)
(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: Ann Johnson, Aerospace Engineer, Wichita Aircraft
Certification Office (ACO), 1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946-4105; fax: (316) 946-4107; E-
mail: ann.johnson@faa.gov. 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.
Material Incorporated by Reference
(g) You must use Cessna Aircraft Company Caravan Service
Bulletin CAB08-9, dated November 24, 2008, to do the actions
required by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita,
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006;
Internet: https://www.cessna.com.
(3) You may review copies of the service information
incorporated by reference for this AD at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the
Central Region, call (816) 329-3768.
(4) You may also review copies of the service information
incorporated by reference for this AD at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on July 6, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-16465 Filed 7-14-09; 8:45 am]
BILLING CODE 4910-13-P
