[Federal Register Volume 76, Number 120 (Wednesday, June 22, 2011)]
[Proposed Rules]
[Pages 36395-36398]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-15543]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0639; Directorate Identifier 2011-CE-016-AD]
RIN 2120-AA64
Airworthiness Directives; Piper Aircraft, Inc. Models PA-24, PA-
24-250, and PA-24-260 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD would require either
replacement of the stabilator horn assembly or repetitive inspection of
the stabilator horn assembly for corrosion or cracks with replacement
of the stabilator horn assembly if any corrosion or cracks are found.
This proposed AD was prompted by reports of cracks developing in the
stabilator horn assembly. We are proposing this AD to detect and
correct corrosion or cracks in the stabilator horn assembly. Corrosion
or cracks could lead to failure of the stabilator horn. Consequently,
failure of the stabilator horn could lead to a loss of pitch control in
flight.
DATES: We must receive comments on this proposed AD by August 8, 2011.
ADDRESSES: You may send comments by any of the following methods:
[[Page 36396]]
Federal eRulemaking Portal: Go to http://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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960;
telephone: (772) 567-4361; fax: (772) 978-6573; Internet: http://www.newpiper.com/company/publications.asp. You may review copies of the
referenced service information at the FAA, Small Airplane Directorate,
901 Locust St., Kansas City, Missouri 64106. For information on the
availability of this material at the FAA, call (816) 329-4148.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Gregory K. Noles, Aerospace Engineer,
FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue,
College Park, Georgia 30337; phone: (404) 474-5551; fax: (404) 474-
5606; e-mail: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2011-0639;
Directorate Identifier 2011-CE-016-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We issued Special Airworthiness Information Bulletin (SAIB) CE-04-
88, dated September 15, 2004. This SAIB alerted owners and operators of
Piper Aircraft, Inc. (Piper) Models PA-23, PA-24, PA-30, and PA-39
airplanes of potential corrosion of the stabilator torque tube, attach
fittings, and attaching fasteners and recommended inspections of these
parts. Based on the information available at issuance of this SAIB, the
FAA had determined that an unsafe condition did not exist under 14 CFR
part 39.
After reviewing service data for corrosion on the stabilator torque
tubes, Piper issued Piper Service Bulletin No. 1160, dated December 26,
2005. This service information is for stabilator torque tube assembly
inspection. We then received reports of cracks found in the stabilator
horn, part number (P/N) 20397-00, during maintenance inspections per
SAIB CE-04-88 or Service Bulletin 1160.
With FAA assistance, the National Institute for Aviation Research
(NIAR) investigated and concluded the root cause of the stabilator horn
cracking was stress corrosion.
We found two service difficulty reports for this safety issue. In
parallel, the International Comanche Society (ICS) surveyed operators
and provided additional service data. The ICS survey included
approximately 80 targeted inspections and found 18 incidences of
stabilator horn cracking, with all incidences occurring on Models PA-24
and PA-24-250 airplanes. The same configuration of horn and torque
assembly exists on Model PA-24-260 airplanes.
This condition, if not corrected, could result in failure of the
stabilator horn. Consequently, failure of the stabilator horn could
lead to a loss of pitch control in flight.
Relevant Service Information
We reviewed Piper Aircraft, Inc. Service Bulletin No. 1189, dated
April 29, 2010. The service information describes procedures for
stabilator horn assembly inspection.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require either replacement of the stabilator
horn assembly or repetitive inspection of the stabilator horn assembly
for corrosion or cracks with replacement of the stabilator horn
assembly if any corrosion or cracks are found.
Differences Between the Proposed AD and the Service Information
The service information requires an initial inspection of the
stabilator horn assembly upon reaching the initial 1,000 hours time-in-
service (TIS), with a repetitive inspection every 100 hours TIS
thereafter. After installation of a new stabilator horn assembly, the
inspection cycle starts over with an initial inspection at 1,000 hours
TIS since the new stabilator horn assembly was installed with the 100-
hour TIS repetitive inspections thereafter.
This proposed AD requires either one of the following options: (1)
An initial inspection of the stabilator horn assembly upon reaching
1,000 hours TIS or within 100 hours TIS after the effective date of the
AD, whichever occurs later, with repetitive inspections every 500 hours
TIS or 3 years, whichever occurs first; or (2) replacement of the
stabilator horn assembly upon reaching 1,000 hours TIS or within the
next 100 hours TIS after the effective date of this AD, whichever
occurs later. After replacement of the stabilator horn assembly, within
1,000 hours TIS or 10 years, whichever occurs first, the stabilator
horn assembly must be replaced or be initially inspected and start the
inspection cycle in option 1.
The service information applies to Piper Models PA-24, PA-24-250,
PA-24-260, PA-24-400, PA-30, and PA-39 airplanes. We only have service
history on Models PA-24 and PA-24-250 airplanes.
While there is no service history of this unsafe condition on Model
PA-24-260 airplanes, we are including it in the AD because it is an
identical configuration to Models PA-24 and PA-24-250 airplanes for the
horn and torque tube.
There is no service history of this unsafe condition on the Models
PA-24-400, PA-30, and PA-39 airplanes, including inspections from the
ICS operator survey. Also, these models have a thicker torque tube,
which reduces clamp-up forces; clamp-up forces are a key factor of the
stress corrosion cracking. Therefore, we are not including the Models
PA-24-400,
[[Page 36397]]
PA-30, and PA-39 airplanes in the applicability of this AD.
Costs of Compliance
We estimate that this proposed AD affects 3,100 airplanes of U.S
registry.
We estimate the following costs to comply with this proposed AD:
Estimated costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Stabilator horn assembly 12 work-hours x $85 Not applicable.......... $1,020 $3,162,000
inspection. per hour = $1,020.
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We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that might need
this replacement:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Stabilator horn assembly replacement....... 12 work-hours x $85 per hour = $572 $1,592
$1,020.
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According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this 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.
For the reasons discussed above, I certify this proposed
regulation:
(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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA 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):
Piper Aircraft, Inc.: Docket No. FAA-2011-0639, Directorate
Identifier 2011-CE-016-AD.
Comments Due Date
(a) We must receive comments by August 8, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following Piper Aircraft, Inc.
airplanes, certificated in any category:
(1) Model PA-24, serial numbers (SNs) 24-1 through 24-3687;
(2) Model PA-24-250, SNs 24-1, 24-103 through 24-3687; and
(3) Model PA-24-260, SNs 24-3642 and 24-4000 through 24-5034.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 27: Flight Controls.
Unsafe Condition
(e) This AD was prompted by reports of cracks developing in the
stabilator horn assembly. We are issuing this AD to detect and
correct corrosion or cracks in the stabilator horn assembly.
Corrosion or cracks could lead to failure of the stabilator horn.
Consequently, failure of the stabilator horn could lead to a loss of
pitch control in flight.
Compliance
(f) Comply with this AD following Piper Aircraft, Inc. Service
Bulletin No. 1189, dated April 29, 2010, within the compliance times
specified in this AD, unless already done (does not eliminate the
repetitive actions of this AD).
Inspection/Replacement
(g) When the stabilator horn assembly reaches a total of 1,000
hours time-in-service (TIS) or within the next 100 hours TIS after
the effective date of this AD, whichever occurs later, do either of
the following actions:
(1) Initially inspect the stabilator horn assembly for corrosion
or cracks. Repetitively thereafter inspect at intervals not to
exceed 500 hours TIS or 3 years, whichever occurs first; or
(2) Replace the stabilator horn assembly with a new stabilator
horn assembly. Repetitively thereafter replace the stabilator horn
assembly with a new stabilator horn assembly within the next 1,000
hours TIS
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after the last replacement or within the next 10 years after the
last replacement, whichever occurs first.
(h) If any corrosion or cracks are found during any of the
inspections required in paragraph (g)(1) of this AD, before further
flight, you must replace the stabilator horn assembly with a new
stabilator horn assembly. After the new stabilator horn assembly
reaches a total of 1,000 hours TIS or within the next 10 years after
the last replacement, whichever occurs first, you must do either of
the actions required in paragraphs (g)(1) or (g)(2) of this AD.
(i) You may at any time replace the stabilator horn assembly
with a new stabilator horn assembly, provided no corrosion or cracks
were found during an inspection that would require replacement
before further flight. After the new stabilator horn assembly
reaches a total of 1,000 hours TIS or within the next 10 years after
the last replacement, whichever occurs first, you must do either of
the actions required in paragraphs (g)(1) or (g)(2) of this AD.
(j) If you replace the stabilator horn assembly as specified in
paragraph (g)(2) of this AD, after the new stabilator horn assembly
reaches a total of 1,000 hours TIS or within the next 10 years after
the last replacement, whichever occurs first, you may begin the
inspection requirements of paragraph (g)(1) instead of the
repetitive replacement requirements of paragraph (g)(2).
Note: Piper Aircraft, Inc. Service Bulletin No. 1160, dated
December 26, 2005; Special Airworthiness Information Bulletin CE-04-
88, dated September 15, 2004; and AD 74-13-03, Amendment 39-2588 (41
FR 17371, April 26, 1976) are related to this AD action. For the
attached torque tube, you may consider combining that inspection
with the requirements of this AD.
Special Flight Permit
(k) Special flight permits are permitted with the following
limitation: flight with known cracks is prohibited.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Atlanta 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. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
Related Information
(m) For more information about this AD, contact Gregory K.
Noles, Aerospace Engineer, FAA, Atlanta ACO, 1701 Columbia Avenue,
College Park, Georgia 30337; phone: (404) 474-5551; fax: (404) 474-
5606; e-mail: [email protected].
(n) For service information identified in this AD, contact Piper
Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960;
telephone: (772) 567-4361; fax: (772) 978-6573; Internet: http://www.newpiper.com/company/publications.asp. You may review copies of
the referenced service information at the FAA, Small Airplane
Directorate, 901 Locust St., Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148.
Issued in Kansas City, Missouri on June 16, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-15543 Filed 6-21-11; 8:45 am]
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