[Federal Register Volume 68, Number 17 (Monday, January 27, 2003)]
[Proposed Rules]
[Pages 3826-3829]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-1679]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-44-AD]
RIN 2120-AA64
Airworthiness Directives; The New Piper Aircraft, Inc. Models PA-
23, PA-23-160, PA-23-235, PA-23-250, and PA-E23-250 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain The New Piper Aircraft, Inc. (Piper)
Models PA-23, PA-23-160, PA-23-235, PA-23-250, and PA-E23-250 airplanes
that do not incorporate a certain design flap control torque tube or
torque tube assembly. This proposed AD would require you to
repetitively inspect the flap control torque tube for cracks,
corrosion, wear, or elongation of the attachment bolt holes (referred
to as damage hereon); and would require you to replace any damaged
torque tube with either an improved design flap control torque tube or
flap control torque tube assembly. The repetitive inspections would no
longer be necessary when the improved design torque tube or torque tube
assembly is installed. This proposed AD is the result of several
reports of damage found in the flap control torque tube on the affected
airplanes. The actions specified by this proposed AD are intended to
detect and correct damage to the flap control torque tube, which could
result in failure of the flap operating system. If such failure
occurred during landing or takeoff, then a split flap condition could
occur with potential loss of control of the airplane.
DATES: The Federal Aviation Administration (FAA) must receive any
[[Page 3827]]
comments on this proposed rule on or before March 21, 2003.
ADDRESSES: Submit comments to FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2002-CE-44-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. You may view any
comments at this location between 8 a.m. and 4 p.m., Monday through
Friday, except Federal holidays. You may also send comments
electronically to the following address: [email protected].
Comments sent electronically must contain ``Docket No. 2002-CE-44-AD''
in the subject line. If you send comments electronically as attached
electronic files, the files must be formatted in Microsoft Word 97 for
Windows or ASCII text.
You may get service information that applies to this proposed AD
from The New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive,
Vero Beach, Florida 32960; telephone: (561) 567-4361; facsimile: (772)
978-6573. You may also view this information at the Rules Docket at the
address above.
FOR FURTHER INFORMATION CONTACT: Hassan Amini, Aerospace Engineer, FAA,
Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix
Boulevard, Suite 450, Atlanta, Georgia 30349; telephone: (770) 703-
6080; facsimile: (770) 703-6097.
SUPPLEMENTARY INFORMATION:
Comments Invited
How Do I Comment On This Proposed AD?
The FAA invites comments on this proposed rule. You may submit
whatever written data, views, or arguments you choose. You need to
include the rule's docket number and submit your comments to the
address specified under the caption ADDRESSES. We will consider all
comments received on or before the closing date. We may amend this
proposed rule in light of comments received. Factual information that
supports your ideas and suggestions is extremely helpful in evaluating
the effectiveness of this proposed AD action and determining whether we
need to take additional rulemaking action.
Are There Any Specific Portions of This Proposed AD I Should Pay
Attention to?
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed rule that
might suggest a need to modify the rule. You may view all comments we
receive before and after the closing date of the rule in the Rules
Docket. We will file a report in the Rules Docket that summarizes each
contact we have with the public that concerns the substantive parts of
this proposed AD.
How Can I Be Sure FAA Receives My Comment?
If you want FAA to acknowledge the receipt of your mailed comments,
you must include a self-addressed, stamped postcard. On the postcard,
write ``Comments to Docket No. 2002-CE-44-AD.'' We will date stamp and
mail the postcard back to you.
Discussion
What Events Have Caused This Proposed AD?
A review of FAA's service difficulty report (SDR) database shows
several incidents of cracks and corrosion in the flap control torque
tube on Piper PA-23 series airplanes. One incident of a broken flap
control torque tube resulted in a split flap condition during approach.
What Are the Consequences If the Condition Is Not Corrected?
Cracked or corroded flap torque tubes, if not detected and
corrected, could result in damage to the flap control torque tube and
failure of the flap operating system. If such failure occurred during
landing or takeoff, then a split flap condition could occur with
potential loss of control of the airplane.
Is There Service Information That Applies to This Subject?
Piper has issued Mandatory Service Bulletin No. 1051B, dated
November 5, 2002.
What Are the Provisions of This Service Information?
The service bulletin includes procedures for:
--Inspecting the flap control torque tube for cracks, corrosion, wear,
or elongation of the attachment bolt holes; and
--Installing a part number (P/N 17634-002 flap control torque tube; or
a P/N 104622-002 or 104622-004 flap control torque tube assembly.
The FAA's Determination and an Explanation of the Provisions of This
Proposed AD
What Has FAA Decided?
After examining the circumstances and reviewing all available
information related to the incidents described above, we have
determined that:
--The unsafe condition referenced in this document exists or could
develop on other Models PA-23, PA-23-160, PA-23-235, PA-23-250, and PA-
E23-250 airplanes of the same type design that do not incorporate a
certain flap control torque tube or torque tube assembly;
--The actions specified in the previously-referenced service
information should be accomplished on the affected airplanes; and
--AD action should be taken in order to correct this unsafe condition.
What Would This Proposed AD Require?
This proposed AD would require you to repetitively inspect the flap
control torque tube for cracks, corrosion, wear, or elongation of the
attachment bolt holes; and would require you to replace any damaged
flap control torque tube with either an improved design flap control
torque tube or flap control torque tube assembly. The repetitive
inspections would no longer be necessary when the improved design flap
control torque tube or flap control torque tube assembly is installed.
Cost Impact
How Many Airplanes Would This Proposed AD Impact?
We estimate that this proposed AD affects 3,733 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 accomplish each proposed
inspection:
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Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
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8 workhours x $60 per hour = $480............ None for inspection............ $480 $1,791,840
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We estimate the following costs to accomplish any necessary
replacement that would be required based on the results of the proposed
inspection. We have no way of determining the number of airplanes that
may need such repair/replacement:
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Total cost per
Labor cost Parts cost airplane
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4 workhours x $60 per hour = $240 $452 per airplane... $692
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Regulatory Impact
Would This Proposed AD Impact Various Entities?
The regulations proposed herein 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. Therefore, it
is determined that this proposed rule would not have federalism
implications under Executive Order 13132.
Would This Proposed AD Involve a Significant Rule or Regulatory Action?
For the reasons discussed above, I certify that this proposed
action (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) if
promulgated, 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. A copy of the draft regulatory
evaluation prepared for this action has been placed in the Rules
Docket. A copy of it may be obtained by contacting the Rules Docket at
the location provided under the caption ADDRESSES.
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
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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. FAA amends Sec. 39.13 by adding a new airworthiness directive
(AD) to read as follows:
The New Piper Aircraft, Inc.: Docket No. 2002-CE-44-AD.
(a) What airplanes are affected by this AD? This AD affects the
following airplane models and serial numbers that are certificated
in any category and do not incorporate a part number (P/N) 17634-002
flap control torque tube; or a P/N 104622-002 or 104622-004 flap
control torque tube assembly:
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Model Serial Nos.
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PA-23 and PA-23-160................. 23-1 through 23-2046.
PA-23-235........................... 27-505 through 27-622.
PA-23-250........................... 27-1 through 27-504 and 27-2000
through 27-8154030.
PA-E23-250.......................... 27-2505 through 27-4916 and 27-
7304917 through 27-7554168.
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(b) Who must comply with this AD? Anyone who wishes to operate
any of the airplanes identified in paragraph (a) of this AD must
comply with this AD.
(c) What problem does this AD address? The actions specified by
this AD are intended to detect and correct damage to the flap
control torque tube, which could result in failure of the flap
operating system. If such failure occurred during landing or
takeoff, then a split flap condition could occur with potential loss
of control of the airplane.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) Inspect the flap control Initially inspect In accordance with
torque tube for cracks, upon accumulating secitons 3 through
corrosion, wear, or 2,500 hours time-in- 10 of the
elongation of the service (TIS) on ACCOMPLISHMENT
attachment bolt holes the flap control INSTRUCTIONS
(referred to as damage torque tube or section of Piper
hereon). within the next 100 Mandatory Service
hours TIS after the Bulletin No. 1051B,
effective date of dated November 5,
this AD, whichever 2002.
occurs later.
Repetitively
inspect thereafter
at intervals not to
exceed 500 hours
TIS until one of
the parts specified
in paragraph (d) of
this AD is
installed.
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(2) Replace any damage flap Prior to further In accordance with
control torque tube and flight after the sections 3 through
replace any wooden end inspection where 10 of the
plugs with new plastic end damage is found. ACCOMPLISHMENT
plugs, P/N 17631-002. INSTRUCTIONS
Replace the flap control section of Piper
torque tubes with either a Mandatory Service
P/N 17634-002 flap control Bulletin No. 1051B,
torque tube or a P/N 104622- dated November 5,
002 or 104622-004 flap 2002.
control torque tube
assembly.
(i) The P/N 17631-002 end
plugs are part of the P/N
104622-002 and 104622-004
flap control torque tube
assemblies, but must be
obtained for the P/N 17634-
002 installation..
(ii) You do not have to
inspect the existing wooden
end plugs as specified in
the service bulletin since
this AD requires the
installation of plastic and
plugs..
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(3) The repetitive You may replace the In accordance with
inspections required by flap control torque sections 3 through
this AD may be terminated tube assembly at 10 of the
after installation of a any time, but must ACCOMPLISHMENT
replacement flap control replace prior to INSTRUCTIONS
torque tube or flap control further flight if section of Piper
torque tube assembly as damage is found Mandatory Service
specified in paragraph (d) during an Bulletin No. 1051B,
of this AD. inspection. dated November 5,
2002.
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[[Page 3829]]
(4) Only install, on As of the effective In accordance with
any affected date of this AD. sections 3 through
airplane, a flap 10 of the
control torque tube ACCOMPLISHMENT
or flap control INSTRUCTIONS
torque tube assembly section of Piper
and end plugs that Mandatory Service
incorporate the part Bulletin No. 1051B,
numbers specified in dated November 5,
paragraph (d) of this 2002.
AD.
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(e) Can I comply with this AD in any other way? You may use an
alternative method of compliance or adjust compliance time if:
(1) Your alternative method of compliance provides an equivalent
level of safety; and
(2) The Manager, Atlanta Aircraft Certification Office, approves
your alternative. Submit your request through an FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Atlanta Aircraft Certification Office.
Note: This AD applies to each airplane identified in paragraph
(a) of this AD, regardless of whether it has been modified, altered,
or repaired in the area subject to the requirements of this AD. For
airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the owner/
operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD;
and, if you have not eliminated the unsafe condition, specific
actions you propose to address it.
(f) Where can I get information about any already-approved
alternative methods of compliance? Contact Hassan Amini, Aerospace
Engineer, FAA, Atlanta Aircraft Certification Office, One Crown
Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349;
telephone: (770) 703-6080; facsimile: (770) 703-6097.
(g) What if I need to fly the airplane to another location to
comply with this AD? The FAA can issue a special flight permit under
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate your airplane to a location where
you can accomplish the requirements of this AD.
(h) How do I get copies of the documents referenced in this AD?
You may get copies of the documents referenced in this AD from The
New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive, Vero
Beach, Florida 32960; telephone: (561) 567-4361; facsimile: (772)
978-6573. You may view these documents at FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106.
Issued in Kansas City, Missouri, on January 15, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, , Aircraft Certification Service.
[FR Doc. 03-1679 Filed 1-24-03; 8:45 am]
BILLING CODE 4910-13-P