Airworthiness Directives; Hawker Beechcraft Corporation Model 1900, 1900C, and 1900D Airplanes, 56710-56713 [E9-26199]
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Federal Register / Vol. 74, No. 211 / Tuesday, November 3, 2009 / Rules and Regulations
7. Inadvertent deployment of the
inflatable lap belt, during the most
critical part of the flight, must be shown
to either not cause a hazard to the
airplane or be extremely improbable.
8. The inflatable lap belt must be
shown to not impede rapid egress of
occupants 10 seconds after its
deployment.
9. The system must be protected from
lightning and HIRF. The threats
specified in existing regulations
regarding lightning, § 25.1316, and
HIRF, § 25.1317, are incorporated by
reference for the purpose of measuring
lightning and HIRF protection. For the
purposes of complying with HIRF
requirements, the inflatable lap-belt
system is considered a ‘‘critical system’’
if its deployment could have a
hazardous effect on the airplane;
otherwise it is considered an ‘‘essential’’
system.
10. The inflatable lap belt must
function properly after loss of normal
aircraft electrical power, and after a
transverse separation of the fuselage at
the most critical location. A separation
at the location of the lap belt does not
have to be considered.
11. The inflatable lap belt must be
shown to not release hazardous
quantities of gas or particulate matter
into the cabin.
12. The inflatable lap-belt installation
must be protected from the effects of fire
such that no hazard to occupants will
result.
13. A means must be available for a
crewmember to verify the integrity of
the inflatable-lap-belt-activation system
prior to each flight or it must be
demonstrated to reliably operate
between inspection intervals.
14. The inflatable material may not
have an average burn rate of greater than
2.5 inches per minute when tested using
the horizontal-flammability test as
defined in 14 CFR part 25, appendix F,
part I, paragraph (b)(5).
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–26356 Filed 11–2–09; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1312; Directorate
Identifier 2008–CE–065–AD; Amendment
39–16072; AD 2009–23–01]
RIN 2120–AA64
Airworthiness Directives; Hawker
Beechcraft Corporation Model 1900,
1900C, and 1900D Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
We are adopting a new
airworthiness directive (AD) for certain
Hawker Beechcraft Corporation Models
1900, 1900C, and 1900D airplanes. This
AD requires a one-time visual
inspection and repetitive ultrasonic
inspections of the left and right main
landing gear (MLG) actuators for leaking
and/or cracks with replacement of the
actuator if leaking and/or cracks are
found. This AD results from reports of
leaking and cracked actuators. We are
issuing this AD to detect and correct
leaking and cracks in the MLG
actuators, which could result in loss of
hydraulic fluid. This condition could
lead to an inability to extend or lock
down the landing gear, which could
result in a gear up landing or a gear
collapse on landing.
DATES: This AD becomes effective on
December 8, 2009.
On December 8, 2009, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: To get the service
information identified in this AD,
contact Hawker Beechcraft Corporation,
P.O. Box 85, Wichita, Kansas 67201–
0085; telephone: (800) 429–5372 or
(316) 676–3140; Internet: https://
pubs.hawkerbeechcraft.com.
To view the AD docket, go to U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590, or on the Internet at https://
www.regulations.gov. The docket
number is FAA–2008–1312; Directorate
Identifier 2008–CE–065–AD.
FOR FURTHER INFORMATION CONTACT: Don
Ristow, Aerospace Engineer, 1801
Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946–
4120; fax: (316) 946–4107.
SUPPLEMENTARY INFORMATION:
SUMMARY:
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Discussion
On August 20, 2009, we issued a
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to
include an AD that would apply to
certain Hawker Beechcraft Corporation
Models 1900, 1900C, and 1900D
airplanes. This proposal was published
in the Federal Register as a
supplemental notice of proposed
rulemaking (NPRM) on August 31, 2009
(74 FR 44773). The NPRM proposed to
require a one-time visual inspection and
repetitive ultrasonic inspections of the
left and right main landing gear (MLG)
actuators for leaking and/or cracks with
replacement of the actuator if leaking
and/or cracks are found.
Comments
We provided the public the
opportunity to participate in developing
this AD. The following presents the
comment received on the proposal and
FAA’s response to the comment:
Comment Issue: Superseding Previous
ADs
Hawker Beechcraft Corporation
requests that with this AD action we
supersede AD 99–04–08 and AD 97–26–
15, which affect earlier configurations of
part number 114–380041 MLG actuator.
They believe that one AD correcting all
of the unsafe conditions concerned with
the MLG actuator would eliminate
confusion concerning which AD to
comply with.
The FAA disagrees. We did consider
supersedure of the previous two ADs,
AD 99–04–08 and AD 97–26–15. The
previous two ADs and this new AD
action each address different unsafe
conditions on the MLG actuators. AD
99–04–08 concerns lubrication and
replacement of the rod end, and AD 97–
26–15 concerns replacement of the
actuator head end cap. This new AD
action concerns replacement of the rod
end cap. AD 99–04–08 uses a prorated
time of compliance starting with
actuators that have accumulated 6,000
hours time-in-service and may still
apply to low usage aircraft or aircraft
that have been in storage. This current
AD action specifies compliance based
on actuator cycles. The only common
feature in the three ADs is that the
actuators were manufactured by Frisby
Airborne Hydraulic, Inc.
Based on the differences in the two
previous ADs and in this new AD, we
determined that combining the three
into a single AD would confuse the
unsafe conditions, rather than simplify
them. If combined into one AD, each
unsafe condition would still have
different inspections, different
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Federal Register / Vol. 74, No. 211 / Tuesday, November 3, 2009 / Rules and Regulations
replacements, and different compliance
times. To incorporate those differences
into a single AD would create a
complicated AD to understand. By
keeping the AD actions separate, the
corrective actions for each unsafe
condition can be complied with
individually. For these reasons, we
decided a new AD action would be
appropriate.
We will not change the final rule AD
action based on this comment.
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
Costs of Compliance
We estimate that this AD affects 300
airplanes in the U.S. registry.
The ultrasonic inspection includes
the time allowed for removing and
reinstalling the actuator. We estimate
the following costs to do the
inspections:
Total cost per
airplane
Labor cost
Parts cost
Visual Inspection: .5 work-hour × $80 per hour = $40 .....................................................
Ultrasonic Inspection: 6 work-hours × $80 per hour = $480 (If the mechanic does not
remove the actuator for the ultrasonic inspection, the labor cost will be less.).
Total cost on
U.S. operators
$40
480
$12,000
144,000
Not applicable ..........
Not applicable ..........
We estimate the following costs to do
any necessary replacements that would
be required based on the results of the
inspections. We have no way of
determining the number of airplanes
that may need this replacement:
Labor cost
Parts cost
6 work-hours × $80 per hour = $480 (If the mechanic removes the actuator for the
ultrasonic inspection, then the labor cost will be less.).
$4,600 per actuator ..................................
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 AD.
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Regulatory Findings
We have 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:
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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 summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2008–1312;
Directorate Identifier 2008–CE–065–
AD’’ in your request.
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 Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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Total cost per
airplane
$5,080
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. FAA amends § 39.13 by adding a
new AD to read as follows:
■
2009–23–01 Hawker Beechcraft
Corporation: Amendment 39–16072;
Docket No. FAA–2008–1312; Directorate
Identifier 2008–CE–065–AD.
Effective Date
(a) This AD becomes effective on December
8, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplane models
and serial numbers listed below that are
certificated in any category and equipped
with a Hawker Beechcraft part number (P/N)
114–380041–11 (or FAA-approved equivalent
P/N), 114–380041–13 (or FAA-approved
equivalent P/N), 114–380041–15 (or FAAapproved equivalent P/N), or 114–380041–
15OVH main landing gear (MLG) actuator.
For the purposes of this AD action the phrase
‘‘or FAA-approved equivalent part number’’
in this AD refers to any PMA part that is
approved by identicality to the referenced
part. Frisby Airborne Hydraulic, Inc. (Frisby)
P/N 1FA10043–3 has parts manufacturer
approval (PMA) by identicality to P/N 114–
380041–15; therefore, it is considered an
FAA-approved equivalent P/N and the AD
applies to airplanes with this part installed.
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Federal Register / Vol. 74, No. 211 / Tuesday, November 3, 2009 / Rules and Regulations
Models
Serial Nos.
(1) 1900 .....................................................
(2) 1900C ...................................................
(3) 1900D ...................................................
UA–3.
UB–1 through UB–74, UC–1 through UC–174, and UD–1 through UD–6.
UE–1 through UE–439.
Unsafe Condition
(d) This AD results from reports of leaking
and cracked actuators. We are issuing this
AD to detect and correct leaking and cracks
in the MLG actuators, which could result in
loss of hydraulic fluid. This condition could
lead to an inability to extend or lock down
the landing gear, which could result in a gear
up landing or a gear collapse on landing.
Compliance
(e) To address this problem, you must do
the following, unless already done:
Note: The phrase ‘‘or FAA-approved
equivalent part number’’ in this AD refers to
any PMA part that is approved by
identicality to the referenced part.
Actions
Compliance
Procedures
(1) Do a one-time visual inspection of the MLG
actuator for cracks.
Within the next 50 hours time-in-service after
December 8, 2009 (the effective date of this
AD) or within the next 30 days after December 8, 2009 (the effective date of this AD),
whichever occurs later.
(2) Do an initial ultrasonic inspection of the
MLG actuator.
Initially within the next 600 cycles after December 8, 2009 (the effective date of this
AD) or within the next 3 months after December 8, 2009 (the effective date of this
AD), whichever occurs first.
(i) For those airplanes with overhauled MLG
actuators (with less than 1,200 cycles) that
have records that prove an internal fluorescent penetrant inspection has been done,
you may do the initial ultrasonic inspection
within the next 600 cycles after December
8, 2009 (the effective date of this AD) or
within the next 1,200 cycles since the last
overhaul, whichever occurs later.
(ii) For those airplanes with MLG actuators
with less than 8,000 cycles since new or
MLG actuators that have records that prove
the end caps are new (less than 8,000 cycles), you may do the initial ultrasonic inspection within the next 1,200 cycles after
December 8, 2009 (the effective date of this
AD) or upon accumulation of 8,000 cycles
since the end caps were new, whichever
occurs later.
Repetitively at intervals not to exceed every
1,200 cycles since the last ultrasonic inspection.
(i) For Hawker Beechcraft parts: Follow Hawker Beechcraft Mandatory Service Bulletin
SB 32–3870, dated April 2008.
(ii) For PMA by identicality: Either contact the
aircraft certification office (ACO) using the
contact information in paragraph (g)(1) of
this AD for FAA-approved procedures provided by the PMA holder; or install Hawker
Beechcraft parts and follow Hawker
Beechcraft Mandatory Service Bulletin SB
32–3870, dated April 2008, and follow any
inspection required by this AD.
(A) For Hawker Beechcraft parts: Follow
Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008.
(B) For PMA by identicality: Either contact the
ACO using the contact information in paragraph (g)(1) of this AD for FAA-approved
procedures provided by the PMA holder; or
install Hawker Beechcraft parts and follow
Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008, and follow any inspection required by this AD.
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(3) For all airplanes, do repetitive ultrasonic inspections of the MLG actuator.
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(i) For Hawker Beechcraft parts: Follow Hawker Beechcraft Mandatory Service Bulletin
SB 32–3870, dated April 2008.
(ii) For PMA by identicality: Either contact the
ACO using the contact information in paragraph (g)(1) of this AD for FAA-approved
procedures provided by the PMA holder; or
install Hawker Beechcraft parts and follow
Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008, and follow any inspection required by this AD.
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Federal Register / Vol. 74, No. 211 / Tuesday, November 3, 2009 / Rules and Regulations
56713
Compliance
Procedures
(4) If cracks are found during any inspection required in paragraph (e)(1), (e)(2), and (e)(3)
of this AD, replace the MLG actuator with
one of the following:
(i) MLG actuator P/N 114–380041–15 (or
FAA-approved equivalent P/N) or 114–
380041–15OVH that is new or has been
inspected following paragraphs (e)(1),
(e)(2), and (e)(3) of this AD and has
been found to not have cracks; or
(ii) An FAA-approved actuator. Installation
of an MLG actuator P/N other than 114–
380041–11 (or FAA-approved equivalent
P/N), 114–380041–13 (or FAA-approved
equivalent P/N), 114–380041–15 (or
FAA-approved equivalent P/N), or 114–
380041–15OVH terminates the inspection requirements of paragraphs (e)(1),
(e)(2), and (e)(3) of this AD.
(5) Do not install any MLG actuator P/N 114–
380041–11 (or FAA-approved equivalent P/
N) or 114–380041–13 (or FAA-approved
equivalent P/N).
Before further flight after the inspection where
the cracks are found.
(A) For Hawker Beechcraft parts: Follow
Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008.
(B) For PMA by identicality: Either contact the
ACO using the contact information in paragraph (g)(1) of this AD for FAA-approved
procedures provided by the PMA holder; or
install Hawker Beechcraft parts and follow
Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008, and follow any inspection required by this AD.
As of December 8, 2009 (the effective date of
this AD).
Not applicable.
(f) If the number of cycles is unknown,
calculate the compliance times of cycles in
this AD by using hours time-in-service (TIS).
Multiply the number of hours TIS on the
MLG actuator by 4 to come up with the
number of cycles. For the purposes of this
AD:
(1) 600 cycles equals 150 hours’ TIS; and
(2) 1,200 cycles equals 300 hours’ TIS.
(g) If cracks are found during any
inspection required in paragraphs (e)(1),
(e)(2), or (e)(3) of this AD, report the size and
location of the cracks to the FAA within 10
days after the cracks are found or within 10
days after December 8, 2009 (the effective
date of this AD), whichever occurs later.
(1) Send report to Don Ristow, Aerospace
Engineer, Wichita ACO, 1801 Airport Road,
Room 100, Wichita, Kansas 67209; e-mail:
donald.ristow@faa.gov.
(2) 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.
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Actions
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 Hawker Beechcraft
Corporation, P.O. Box 85, Wichita, Kansas
67201–0085; telephone: (800) 429–5372 or
(316) 676–3140; Internet: https://
pubs.hawkerbeechcraft.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.
DEPARTMENT OF TRANSPORTATION
Alternative Methods of Compliance
(AMOCs)
(h) 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: Don
Ristow, Aerospace Engineer, 1801 Airport
Road, Room 100, Wichita, Kansas 67209;
telephone: (316) 946–4120; fax: (316) 946–
4107. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Kansas City, Missouri, on
October 23, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9–26199 Filed 11–2–09; 8:45 am]
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14 CFR Part 39
[Docket No. FAA–2009–0999; Directorate
Identifier 2009–NM–155–AD; Amendment
39–16069; AD 2008–04–19 R1]
RIN 2120–AA64
Airworthiness Directives; ATR Model
ATR42 and ATR72 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above that would revise
an existing AD. 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:
Subsequent to accidents involving Fuel
Tank System explosions in flight * * * and
on ground, * * * Special Federal Aviation
Regulation 88 (SFAR88) * * * required a
safety review of the aircraft Fuel Tank
System * * *.
*
*
*
*
*
Fuel Airworthiness Limitations are items
arising from a systems safety analysis that
have been shown to have failure mode(s)
associated with an ‘unsafe condition’ * * *.
These are identified in Failure Conditions for
which an unacceptable probability of ignition
risk could exist if specific tasks and/or
Material Incorporated by Reference
(i) You must use Hawker Beechcraft
Mandatory Service Bulletin SB 32–3870,
dated April 2008, to do the actions required
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Federal Aviation Administration
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]]>Agencies
[Federal Register Volume 74, Number 211 (Tuesday, November 3, 2009)]
[Rules and Regulations]
[Pages 56710-56713]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-26199]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1312; Directorate Identifier 2008-CE-065-AD;
Amendment 39-16072; AD 2009-23-01]
RIN 2120-AA64
Airworthiness Directives; Hawker Beechcraft Corporation Model
1900, 1900C, and 1900D Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes.
This AD requires a one-time visual inspection and repetitive ultrasonic
inspections of the left and right main landing gear (MLG) actuators for
leaking and/or cracks with replacement of the actuator if leaking and/
or cracks are found. This AD results from reports of leaking and
cracked actuators. We are issuing this AD to detect and correct leaking
and cracks in the MLG actuators, which could result in loss of
hydraulic fluid. This condition could lead to an inability to extend or
lock down the landing gear, which could result in a gear up landing or
a gear collapse on landing.
DATES: This AD becomes effective on December 8, 2009.
On December 8, 2009, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in this
AD.
ADDRESSES: To get the service information identified in this AD,
contact Hawker Beechcraft Corporation, P.O. Box 85, Wichita, Kansas
67201-0085; telephone: (800) 429-5372 or (316) 676-3140; Internet:
https://pubs.hawkerbeechcraft.com.
To view the AD docket, go to U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at
https://www.regulations.gov. The docket number is FAA-2008-1312;
Directorate Identifier 2008-CE-065-AD.
FOR FURTHER INFORMATION CONTACT: Don Ristow, Aerospace Engineer, 1801
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4120; fax: (316) 946-4107.
SUPPLEMENTARY INFORMATION:
Discussion
On August 20, 2009, we issued a proposal to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) to include an AD that
would apply to certain Hawker Beechcraft Corporation Models 1900,
1900C, and 1900D airplanes. This proposal was published in the Federal
Register as a supplemental notice of proposed rulemaking (NPRM) on
August 31, 2009 (74 FR 44773). The NPRM proposed to require a one-time
visual inspection and repetitive ultrasonic inspections of the left and
right main landing gear (MLG) actuators for leaking and/or cracks with
replacement of the actuator if leaking and/or cracks are found.
Comments
We provided the public the opportunity to participate in developing
this AD. The following presents the comment received on the proposal
and FAA's response to the comment:
Comment Issue: Superseding Previous ADs
Hawker Beechcraft Corporation requests that with this AD action we
supersede AD 99-04-08 and AD 97-26-15, which affect earlier
configurations of part number 114-380041 MLG actuator. They believe
that one AD correcting all of the unsafe conditions concerned with the
MLG actuator would eliminate confusion concerning which AD to comply
with.
The FAA disagrees. We did consider supersedure of the previous two
ADs, AD 99-04-08 and AD 97-26-15. The previous two ADs and this new AD
action each address different unsafe conditions on the MLG actuators.
AD 99-04-08 concerns lubrication and replacement of the rod end, and AD
97-26-15 concerns replacement of the actuator head end cap. This new AD
action concerns replacement of the rod end cap. AD 99-04-08 uses a
prorated time of compliance starting with actuators that have
accumulated 6,000 hours time-in-service and may still apply to low
usage aircraft or aircraft that have been in storage. This current AD
action specifies compliance based on actuator cycles. The only common
feature in the three ADs is that the actuators were manufactured by
Frisby Airborne Hydraulic, Inc.
Based on the differences in the two previous ADs and in this new
AD, we determined that combining the three into a single AD would
confuse the unsafe conditions, rather than simplify them. If combined
into one AD, each unsafe condition would still have different
inspections, different
[[Page 56711]]
replacements, and different compliance times. To incorporate those
differences into a single AD would create a complicated AD to
understand. By keeping the AD actions separate, the corrective actions
for each unsafe condition can be complied with individually. For these
reasons, we decided a new AD action would be appropriate.
We will not change the final rule AD action based on this comment.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed
except for minor editorial corrections. We have determined that these
minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 300 airplanes in the U.S.
registry.
The ultrasonic inspection includes the time allowed for removing
and reinstalling the actuator. We estimate the following costs to do
the inspections:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
----------------------------------------------------------------------------------------------------------------
Visual Inspection: .5 work-hour x $80 per hour Not applicable.................. $40 $12,000
= $40.
Ultrasonic Inspection: 6 work-hours x $80 per Not applicable.................. 480 144,000
hour = $480 (If the mechanic does not remove
the actuator for the ultrasonic inspection,
the labor cost will be less.).
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspections. We have
no way of determining the number of airplanes that may need this
replacement:
------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
6 work-hours x $80 per hour = $480 $4,600 per actuator. $5,080
(If the mechanic removes the
actuator for the ultrasonic
inspection, then the labor cost
will be less.).
------------------------------------------------------------------------
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 AD.
Regulatory Findings
We have 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 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 summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2008-1312; Directorate Identifier 2008-CE-065-AD'' in your
request.
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 Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (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. FAA amends Sec. 39.13 by adding a new AD to read as follows:
2009-23-01 Hawker Beechcraft Corporation: Amendment 39-16072; Docket
No. FAA-2008-1312; Directorate Identifier 2008-CE-065-AD.
Effective Date
(a) This AD becomes effective on December 8, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplane models and serial numbers
listed below that are certificated in any category and equipped with
a Hawker Beechcraft part number (P/N) 114-380041-11 (or FAA-approved
equivalent P/N), 114-380041-13 (or FAA-approved equivalent P/N),
114-380041-15 (or FAA-approved equivalent P/N), or 114-380041-15OVH
main landing gear (MLG) actuator. For the purposes of this AD action
the phrase ``or FAA-approved equivalent part number'' in this AD
refers to any PMA part that is approved by identicality to the
referenced part. Frisby Airborne Hydraulic, Inc. (Frisby) P/N
1FA10043-3 has parts manufacturer approval (PMA) by identicality to
P/N 114-380041-15; therefore, it is considered an FAA-approved
equivalent P/N and the AD applies to airplanes with this part
installed.
[[Page 56712]]
----------------------------------------------------------------------------------------------------------------
Models Serial Nos.
----------------------------------------------------------------------------------------------------------------
(1) 1900.................................................... UA-3.
(2) 1900C................................................... UB-1 through UB-74, UC-1 through UC-174, and UD-1
through UD-6.
(3) 1900D................................................... UE-1 through UE-439.
----------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from reports of leaking and cracked
actuators. We are issuing this AD to detect and correct leaking and
cracks in the MLG actuators, which could result in loss of hydraulic
fluid. This condition could lead to an inability to extend or lock
down the landing gear, which could result in a gear up landing or a
gear collapse on landing.
Compliance
(e) To address this problem, you must do the following, unless
already done:
Note: The phrase ``or FAA-approved equivalent part number'' in
this AD refers to any PMA part that is approved by identicality to
the referenced part.
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Do a one-time visual Within the next 50 hours (i) For Hawker
inspection of the MLG time-in-service after Beechcraft
actuator for cracks. December 8, 2009 (the parts: Follow
effective date of this Hawker
AD) or within the next 30 Beechcraft
days after December 8, Mandatory
2009 (the effective date Service
of this AD), whichever Bulletin SB 32-
occurs later. 3870, dated
April 2008.
(ii) For PMA by
identicality:
Either contact
the aircraft
certification
office (ACO)
using the
contact
information in
paragraph
(g)(1) of this
AD for FAA-
approved
procedures
provided by the
PMA holder; or
install Hawker
Beechcraft
parts and
follow Hawker
Beechcraft
Mandatory
Service
Bulletin SB 32-
3870, dated
April 2008, and
follow any
inspection
required by
this AD.
(2) Do an initial Initially within the next (A) For Hawker
ultrasonic inspection of 600 cycles after December Beechcraft
the MLG actuator. 8, 2009 (the effective parts: Follow
date of this AD) or Hawker
within the next 3 months Beechcraft
after December 8, 2009 Mandatory
(the effective date of Service
this AD), whichever Bulletin SB 32-
occurs first. 3870, dated
(i) For those airplanes April 2008.
with overhauled MLG (B) For PMA by
actuators (with less than identicality:
1,200 cycles) that have Either contact
records that prove an the ACO using
internal fluorescent the contact
penetrant inspection has information in
been done, you may do the paragraph
initial ultrasonic (g)(1) of this
inspection within the AD for FAA-
next 600 cycles after approved
December 8, 2009 (the procedures
effective date of this provided by the
AD) or within the next PMA holder; or
1,200 cycles since the install Hawker
last overhaul, whichever Beechcraft
occurs later. parts and
(ii) For those airplanes follow Hawker
with MLG actuators with Beechcraft
less than 8,000 cycles Mandatory
since new or MLG Service
actuators that have Bulletin SB 32-
records that prove the 3870, dated
end caps are new (less April 2008, and
than 8,000 cycles), you follow any
may do the initial inspection
ultrasonic inspection required by
within the next 1,200 this AD.
cycles after December 8,
2009 (the effective date
of this AD) or upon
accumulation of 8,000
cycles since the end caps
were new, whichever
occurs later.
(3) For all airplanes, do Repetitively at intervals (i) For Hawker
repetitive ultrasonic not to exceed every 1,200 Beechcraft
inspections of the MLG cycles since the last parts: Follow
actuator. ultrasonic inspection. Hawker
Beechcraft
Mandatory
Service
Bulletin SB 32-
3870, dated
April 2008.
(ii) For PMA by
identicality:
Either contact
the ACO using
the contact
information in
paragraph
(g)(1) of this
AD for FAA-
approved
procedures
provided by the
PMA holder; or
install Hawker
Beechcraft
parts and
follow Hawker
Beechcraft
Mandatory
Service
Bulletin SB 32-
3870, dated
April 2008, and
follow any
inspection
required by
this AD.
[[Page 56713]]
(4) If cracks are found Before further flight (A) For Hawker
during any inspection after the inspection Beechcraft
required in paragraph where the cracks are parts: Follow
(e)(1), (e)(2), and found. Hawker
(e)(3) of this AD, Beechcraft
replace the MLG actuator Mandatory
with one of the Service
following: Bulletin SB 32-
(i) MLG actuator P/N 114- 3870, dated
380041-15 (or FAA- April 2008.
approved equivalent P/N) (B) For PMA by
or 114-380041-15OVH that identicality:
is new or has been Either contact
inspected following the ACO using
paragraphs (e)(1), the contact
(e)(2), and (e)(3) of information in
this AD and has been paragraph
found to not have cracks; (g)(1) of this
or AD for FAA-
(ii) An FAA-approved approved
actuator. Installation of procedures
an MLG actuator P/N other provided by the
than 114-380041-11 (or PMA holder; or
FAA-approved equivalent P/ install Hawker
N), 114-380041-13 (or FAA- Beechcraft
approved equivalent P/N), parts and
114-380041-15 (or FAA- follow Hawker
approved equivalent P/N), Beechcraft
or 114-380041-15OVH Mandatory
terminates the inspection Service
requirements of Bulletin SB 32-
paragraphs (e)(1), 3870, dated
(e)(2), and (e)(3) of April 2008, and
this AD. follow any
inspection
required by
this AD.
(5) Do not install any MLG As of December 8, 2009 Not applicable.
actuator P/N 114-380041- (the effective date of
11 (or FAA-approved this AD).
equivalent P/N) or 114-
380041-13 (or FAA-
approved equivalent P/N).
------------------------------------------------------------------------
(f) If the number of cycles is unknown, calculate the
compliance times of cycles in this AD by using hours time-in-service
(TIS). Multiply the number of hours TIS on the MLG actuator by 4 to
come up with the number of cycles. For the purposes of this AD:
(1) 600 cycles equals 150 hours' TIS; and
(2) 1,200 cycles equals 300 hours' TIS.
(g) If cracks are found during any inspection required in
paragraphs (e)(1), (e)(2), or (e)(3) of this AD, report the size and
location of the cracks to the FAA within 10 days after the cracks
are found or within 10 days after December 8, 2009 (the effective
date of this AD), whichever occurs later.
(1) Send report to Don Ristow, Aerospace Engineer, Wichita ACO,
1801 Airport Road, Room 100, Wichita, Kansas 67209; e-mail:
donald.ristow@faa.gov.
(2) 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.
Alternative Methods of Compliance (AMOCs)
(h) 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: Don Ristow, Aerospace Engineer, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4120; fax: (316) 946-
4107. Before using any approved AMOC on any airplane to which the
AMOC applies, notify your appropriate principal inspector (PI) in
the FAA Flight Standards District Office (FSDO), or lacking a PI,
your local FSDO.
Material Incorporated by Reference
(i) You must use Hawker Beechcraft Mandatory Service Bulletin SB
32-3870, dated April 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
Hawker Beechcraft Corporation, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140; Internet: https://pubs.hawkerbeechcraft.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 October 23, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-26199 Filed 11-2-09; 8:45 am]
BILLING CODE 4910-13-P
