[Federal Register: September 15, 2005 (Volume 70, Number 178)]
[Rules and Regulations]
[Page 54472-54474]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15se05-3]
[[Page 54472]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21410; Directorate Identifier 2005-CE-31-AD;
Amendment 39-14272; AD 2005-19-07]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Model 390
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain
Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD
requires you to replace the rudder pedal arm assemblies used in the
rudder control system with parts of improved design. This AD results
from reports of cracks found on the rudder pedal arm assemblies. We are
issuing this AD to prevent failure of the rudder pedal arm assemblies
caused by fatigue cracks. This failure could lead to loss of rudder
control, loss of nose gear steering, and loss of toe brakes on the side
on which the failure occurs.
DATES: This AD becomes effective on October 31, 2005.
As of October 31, 2005, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
ADDRESSES: To get the service information identified in this AD,
contact Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas
67201-0085; telephone: (800) 429-5372 or (316) 676-3140.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov.
The docket number is FAA-2005-21410; Directorate
Identifier 2005-CE-31-AD.
FOR FURTHER INFORMATION CONTACT: David Ostrodka, Aerospace Engineer,
Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road,
Wichita, Kansas 67209; telephone: (316) 946-4129; facsimile: (316) 946-
4107; e-mail: david.ostrodka@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? Raytheon received a report that,
during ground maintenance operations, the pilot's outboard rudder pedal
arm assembly cracked at the upper end of the arm.
While maneuvering the aircraft from a right turn to neutral with
toe brake applied during an on-ground compass swing, the rudder pedal
arm assembly cracked.
Further investigation revealed another airplane with a crack on the
copilot's outboard rudder pedal arm assembly.
Raytheon has determined that loading of the rudder pedals off the
centerline of the rudder pedal arm assembly results in overload, which
causes fatigue cracking of the rudder pedal arm assembly.
What is the potential impact if FAA took no action? If not
prevented, cracks in the rudder pedal arm assembly could cause the
rudder pedal arm assembly to fail. This failure could lead to loss of
rudder control, loss of nose gear steering, and loss of toe brakes on
the side on which the failure occurs.
Has FAA taken any action to this point? 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 Raytheon Model 390 airplanes.
This proposal was published in the Federal Register as a notice of
proposed rulemaking (NPRM) on June 20, 2005 (70 FR 35385). The NPRM
proposed to require you to replace the rudder pedal arm assemblies,
part numbers (P/Ns) 390-524350-0001, 390-524350-0002, 390-524351-0001,
and 390-524351-0002 with improved design parts, P/Ns 390-524400-0001,
390-524400-0002, 390-524401-0003, and 390-524401-0004.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. We received no
comments on the proposal or on the determination of the cost to the
public.
Conclusion
What is FAA's final determination on this issue? 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.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 98 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to accomplish the
modification:
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Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
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8 work hours x $65 per hour = $520.. $1,165 $1,685 $1,685 x 98 = $165,130.
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Raytheon will provide warranty credit for parts and labor to the
extent stated in the service information. Therefore, the required
actions, if done following the service information, will have little or
no cost to the owners/operators of the affected airplanes.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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
[[Page 54473]]
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
Will this AD impact various entities? 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.
Will this AD involve a significant rule or regulatory action? 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-2005-21410; Directorate Identifier 2005-CE-31-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:
2005-19-07 Raytheon Aircraft Company: Amendment 39-14272; Docket No.
FAA-2005-21410; Directorate Identifier 2005-CE-31-AD.
When Does This AD Become Effective?
(a) This AD becomes effective on October 31, 2005.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects the following serial-numbered Model 390
airplanes that are certificated in any category:
Serial Numbers
(1) RB-1
(2) RB-4 through RB-36
(3) RB-38 through RB-41
(4) RB-43 through RB-67
(5) RB-69 through RB-80
(6) RB-82 through RB-84
(7) RB-87 through RB-94
(8) RB-96 through RB-101
(9) RB-103 through RB-115
(10) RB-117 through RB-119
(11) RB-121
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of reports of cracks found on the
rudder pedal arm assemblies used in the rudder control system. The
actions specified in this AD are intended to prevent failure of the
rudder pedal arm assemblies caused by fatigue cracks. This failure
could lead to loss of rudder control, loss of nose gear steering,
and loss of toe brakes on the side on which the failure occurs.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
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Actions Compliance Procedures
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(1) Replace rudder pedal arm Upon accumulating Follow Raytheon
assemblies, part numbers (P/ 300 hours time-in- Aircraft Company
Ns) 390-524350-0001, 390- service (TIS) or Mandatory Service
524350-0002, 390-524351- within 100 hours Bulletin, SB 27-
0001, and 390-524351-0002 TIS after October 3691, Rev. 1,
with improved design parts, 31, 2005 (the Revised: February,
P/Ns 390-524400-0001, 390- effective date of 2005, and the
524400-0002, 390-524401- this AD), whichever applicable
0003, and 390-524401-0004. occurs later, maintenance manual.
unless already done.
(2) Do not install rudder As of October 31, Not applicable.
pedal arm assemblies, P/Ns 2005 (the effective
390-524350-0001, 390-524350- date of this AD).
0002, 390-524351-0001, and
390-524351-0002.
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Note: Replacing the rudder pedal arm assemblies following
Raytheon Aircraft Company Mandatory Service Bulletin, SB 27-3691,
Issued: October 2004, does not comply with this AD.
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to
your principal inspector. The principal inspector may add comments
and will send your request to the Manager, Wichita Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance, contact David Ostrodka,
Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita,
Kansas 67209; telephone: (316) 946-4129; facsimile: (316) 946-4107;
e-mail: david.ostrodka@faa.gov.
Does This AD Incorporate Any Material by Reference?
(g) You must do the actions required by this AD following the
instructions in Raytheon Aircraft Company Mandatory Service
Bulletin, SB 27-3691, Rev. 1, Revised: February, 2005. The Director
of the Federal Register approved the incorporation by reference of
this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get a copy of this service information, contact Raytheon
Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-0085;
telephone: (800) 429-5372 or (316) 676-3140. To review copies of
this service information, go to the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
or call (202)
741-6030. To view the AD docket, go to the Docket Management
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on
the Internet at http://dms.dot.gov. The docket number is FAA-2005-
21410; Directorate Identifier 2005-CE-31-AD.
[[Page 54474]]
Issued in Kansas City, Missouri, on September 8, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-18199 Filed 9-14-05; 8:45 am]
BILLING CODE 4910-13-P