[Federal Register: November 22, 2005 (Volume 70, Number 224)]
[Proposed Rules]
[Page 70555-70557]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22no05-19]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 70555]]
DEPARTMENT OF TRANSPORTATION (DOT)
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21175; Directorate Identifier 2005-CE-24-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company Models 58P
and 58TC Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Raytheon Aircraft Company (Raytheon) Models 58P and 58TC
airplanes used as a lead airplane by the United States Forest Service.
This proposed AD would require you to insert a new supplement into the
Limitations Section of the Pilot's Operating Handbook and Airplane
Flight Manual (POH/AFM) that establishes new limits for the structural
life of the airframe (wing, fuselage, empennage, or associated
structure); and dispose of the life-limited airframe following 14 CFR
43.10 when the limit of the structural life of the airframe is reached.
This proposed AD results from Raytheon issuing a POH/AFM supplement
that establishes the structural life limit of 4,500 hours time-in-
service (TIS) for the airframe (wing, fuselage, empennage, and
associated structure) for any Models 58P and 58TC airplanes used as a
lead airplane by the United States Forest Service; and FAA's
determination that the structural life limit is necessary. We are
issuing this proposed AD to prevent cumulative fatigue damage and
fatigue cracking damage that would sufficiently reduce residual
strength of the airframe and result in failure. Failure of the airframe
(wing, fuselage, empennage, or associated structure) could lead to loss
of control of the airplane.
DATES: We must receive any comments on this proposed AD by January 23,
2006.
ADDRESSES: Use one of the following to submit comments on this proposed
AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: 1-202-493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
To get the service information identified in this proposed AD,
contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140.
To view the comments to this proposed AD, go to http://dms.dot.gov.
The docket number is FAA-2005-21175; Directorate Identifier 2005-CE-24-
AD.
FOR FURTHER INFORMATION CONTACT: Steven E. Potter, Aerospace Engineer,
Wichita Aircraft Certification Office (ACO), FAA, 1801 Airport Road,
Wichita, Kansas 67209; telephone: (316) 946-4124; facsimile: (316) 946-
4107.
SUPPLEMENTARY INFORMATION:
Comments Invited
How do I comment on this proposed AD? We invite you to submit any
written relevant data, views, or arguments regarding this proposal.
Send your comments to an address listed under ADDRESSES. Include the
docket number, ``FAA-2005-21175; Directorate Identifier 2005-CE-24-AD''
at the beginning of your comments. We will post all comments we
receive, without change, to http://dms.dot.gov, including any personal
information you provide. We will also post a report summarizing each
substantive verbal contact with FAA personnel concerning this proposed
rulemaking. Using the search function of our docket Web site, anyone
can find and read the comments received into any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
This is docket number FAA-2005-21175; Directorate Identifier 2005-CE-
24-AD. You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit http://dms.dot.gov.
Are there any specific portions of this proposed AD I should pay
attention to? We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of this
proposed AD. If you contact us through a nonwritten communication and
that contact relates to a substantive part of this proposed AD, we will
summarize the contact and place the summary in the docket. We will
consider all comments received by the closing date and may amend this
proposed AD in light of those comments and contacts.
Docket Information
Where can I go to view the docket information? You may view the AD
docket that contains the proposal, any comments received, and any final
disposition in person at the DMS Docket Offices between 9 a.m. and 5
p.m. (eastern time), Monday through Friday, except Federal holidays.
The Docket Office (telephone 1-800-647-5227) is located on the plaza
level of the Department of Transportation NASSIF Building at the street
address stated in ADDRESSES. You may also view the AD docket on the
Internet at http://dms.dot.gov. The comments will be available in the
AD docket shortly after the DMS receives them.
Discussion
What events have caused this proposed AD? The type certificate of
the Models 58P and 58TC airplanes establishes (in the Limitations
Section of the FAA Approved Airplane Flight Manual) a structural life
limit of 10,000 hours time-in-service (TIS). This life limit was
established by using the standard and expected usage for normal twin-
engine usage envelopes and industry standard approaches for fatigue
testing and analysis, structural fatigue analysis reports, ground
structural
[[Page 70556]]
fatigue test reports, and flight test fatigue spectrum monitoring
reports.
The United States Forest Service (USFS) bought the 21 airplanes
identified in this NPRM for use as lead airplanes for the forest
firefighting mission. Operation in the lead airplane firefighting
mission is a more severe usage than the normal usage of twin-engine
aircraft.
In October 2004, the USFS informed FAA that it was to dispose of
these airplanes through the General Services Administration (GSA).
In January 2005, Raytheon issued a supplement for the Limitations
Section of the Pilot's Operating Handbook and Airplane Flight Manual
(POH/AFM) that reduces the original type certification structural
fatigue life limit to 4,500 hours TIS. The latest revisions of the
analytical reports by Raytheon and USFS are dated July 1984.
The FAA has determined that if flight operations continue beyond
4,500 hours TIS, then the cumulative fatigue damage on these airplanes
will reach a point at which fatigue cracking might occur. This damage
will reduce residual strength and deplete all useful service life.
Operation of these airplanes in a severe fatigue-loading spectrum
accelerates the cumulative fatigue damage. This higher fatigue damage
accumulation rate experienced by the USFS (operation in the lead
airplane firefighting mission) is higher than normal usage and results
in a shorter life limit. The severity of the usage by the USFS reduced
the structural life limit.
The Service Difficulty Reports (SDR) database indicates some wing
skin cracking, pressure bulkhead cracking, and cracking in both the
vertical and horizontal stabilizers. A significant number of these
cracking occurrences were on the subject airplanes. We believe that the
SDR database does not reflect all such occurrences on the subject
airplanes.
What is the potential impact if FAA took no action? Cumulative
fatigue damage causing fatigue cracking damage would sufficiently
reduce the residual strength of the airframe. Failure of the airframe
(wing, fuselage, empennage, or associated structure) could lead to
failure with a consequent loss of control of the airplane.
Is there service information that applies to this subject? Raytheon
has issued Beechcraft Model 58P/58PA and Model 58TC/58TCA Pilot's
Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM)
Supplement, part number (P/N) 102-590000-67, issued January 2005.
This supplement affects Models 58P and 58TC airplanes used as a
lead airplane by the USFS with these serial numbers: TJ-177, TJ-178,
TJ-180, TJ-211, TJ-213, TJ-247, TJ-284, TJ-285, TJ-289, TJ-290, TJ-314,
TJ-322, TJ-367, TJ-368, TJ-370, TJ-371, TJ-425, TJ-426, TJ-433, TJ-442,
and TK-33.
FAA's Determination and Requirements of This Proposed AD
What has FAA decided? We have evaluated all pertinent information
and identified an unsafe condition that is likely to exist or develop
on other products of this same type design. For this reason, we are
proposing AD action.
What would this proposed AD require? This proposed AD would require
you to:
--Insert the Raytheon Aircraft Company Beechcraft Model 58P/58PA and
Model 58TC/58TCA POH/AFM Supplement, part number (P/N) 102-590000-67,
issued January 2005, into the Limitations Section of the POH/AFM (P/N
102-590000-41 or 106-590000-5). This limits the structural life of the
airframe (wing, fuselage, empennage, and associated structure) to 4,500
hours time-in-service (TIS); and
--Dispose of the life-limited airframe (wing, fuselage, empennage, and
associated structure) following 14 CFR 43.10 when the limit (4,500
hours TIS) of the structural life of the airframe is reached.
How does the revision to 14 CFR part 39 affect this proposed AD? On
July 10, 2002, we published a new version of 14 CFR part 39 (67 FR
47997, July 22, 2002), which governs 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 would this proposed AD impact? We estimate that
this proposed AD affects 21 airplanes in the U.S. registry.
What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to
incorporate the Raytheon Aircraft Company Beechcraft Model 58P/58PA and
Model 58TC/58TCA POH/AFM Supplement into the POH/AFM:
----------------------------------------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
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1 work hour x $65 per hour = $65............. Not applicable................. $65 $1,365
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We estimate the cost to dispose of the life-limited airframe (wing,
fuselage, empennage, and associated structure) following 14 CFR 43.10
(when the limit of the structural life of the airframe is reached) to
be the cost of each airplane.
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
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
Would this proposed AD impact various entities? We have determined
that this proposed AD would not have federalism implications under
Executive Order 13132. This proposed AD would not have a substantial
direct effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and
responsibilities among the various levels of government.
Would this proposed AD involve a significant rule or regulatory
action? For the reasons discussed above, I certify that this proposed
AD:
[[Page 70557]]
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 proposed 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-2005-21175; Directorate Identifier 2005-CE-24-AD'' in
your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Raytheon Aircraft Company: Docket No. FAA-2005-21175; Directorate
Identifier 2005-CE-24-AD.
When Is the Last Date I Can Submit Comments on This Proposed AD?
(a) We must receive comments on this proposed airworthiness
directive (AD) by January 23, 2006.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Models 58P and 58TC airplanes, with the
following serial numbers: TJ-177, TJ-178, TJ-180, TJ-211, TJ-213,
TJ-247, TJ-284, TJ-285, TJ-289, TJ-290, TJ-314, TJ-322, TJ-367, TJ-
368, TJ-370, TJ-371, TJ-425, TJ-426, TJ-433, TJ-442, and TK-33, that
are certificated in any category. These airplanes were utilized as
lead airplanes by the United States Forest Service for firefighting
missions.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of Raytheon issuing a Pilot's
Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM)
Supplement that establishes the structural life of 4,500 hours time-
in-service (TIS) for the airframe (wing, fuselage, empennage, and
associated structure), and FAA's determination that the structural
life is necessary. The actions specified in this AD are intended to
prevent cumulative fatigue damage and fatigue cracking damage that
would sufficiently reduce residual strength of the airframe and
result in failure. Failure of the airframe (wing, fuselage,
empennage, or associated structure) could lead to loss of control of
the airplane.
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) Insert the Raytheon Upon the The owner/operator
Aircraft Company Beechcraft accumulation of holding at least a
Model 58P/58PA and Model 4,500 hours TIS on private pilot
58TC/58TCA Pilot's the airframe (wing, certificate as
Operating Handbook and FAA fuselage, authorized by
Approved Airplane Flight empennage, or section 43.7 of the
Manual (POH/AFM) associated Federal Aviation
Supplement, part number (P/ structure) or prior Regulations (14 CFR
N) 102-590000-67, issued to further flight, 43.7) may modify
January 2005, into the POH/ whichever occurs the POH as
AFM (P/N 102-590000-41 or later, unless specified in
106-590000-5). The already done. paragraph (e)(1) of
Limitations Section limits this AD. Make an
the structural life of the entry into the
airframe (wing, fuselage, aircraft records
empennage, and associated showing compliance
structure) to 4,500 hours with this portion
time-in-service (TIS). of the AD following
section 43.9 of the
Federal Aviation
Regulations (14 CFR
43.9).
(2) Dispose of the life- Upon the Follow section 43.10
limited airframe (wing, accumulation of of the Federal
fuselage, empennage, and 4,500 hours TIS on Aviation
associated structure) the airframe (wing, Regulations (14 CFR
following 14 CFR 43.10 when fuselage, 43.10).
the limit of the structural empennage, or
life of the airframe is associated
reached. structure) or prior
to further flight,
whichever occurs
later, unless
already done.
(3) Do not operate any As of the effective Not applicable.
Models 58P and 58TC date of this AD.
airplanes (with any serial
number noted in paragraph
(c) of this AD0 upon the
accumulation of 4,500 hours
TIS on the airframe (wing,
fuselage, empennage, or
associated structure).
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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 Steven E.
Potter, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road,
Wichita, Kansas 67209; telephone: (316) 946-4124; facsimile: (316)
946-4107.
May I Get Copies of the Documents Referenced in This AD?
(g) To get copies of the documents referenced in this AD,
contact Raytheon Aircraft Company, P.O. Box 85, 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, or on the Internet at http://dms.dot.gov. The
docket number is Docket No. FAA-2005-21175; Directorate Identifier
2005-CE-24-AD.
Issued in Kansas City, Missouri, on November 16, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23055 Filed 11-21-05; 8:45 am]
BILLING CODE 4910-13-P