[Federal Register Volume 63, Number 182 (Monday, September 21, 1998)]
[Proposed Rules]
[Pages 50174-50176]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-25127]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-152-AD]
RIN 2120-AA64
Airworthiness Directives; The New Piper Aircraft, Inc. Models PA-
31, PA-31-300, PA-31-325, PA-31-350, and PA-31P-350 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede Airworthiness Directive
(AD) 81-15-04 R1, which applies to certain The New Piper Aircraft, Inc.
(Piper) Models PA-31, PA-31-300, PA-31-325, PA-31-350, and PA-31P-350
airplanes and currently requires repetitively inspecting for cracks at
the elevator outboard hinge attachment on the horizontal stabilizer
rear spar, and if cracks are found, incorporating a spar and hinge
bracket assembly kit. The proposed action would require repetitively
inspecting the horizontal rear spar in the area of the outboard hinge
attachment and the outboard hinge attach bracket for cracks. When
cracks are found or at a certain accumulation of time-in-service (TIS),
the proposed AD would require modifying the horizontal stabilizer spar
by incorporating an improved stabilizer spar and hinge bracket assembly
kit that would terminate the repetitive inspections. The proposed AD is
prompted by several field reports of cracks found during routine
inspections on airplanes already in compliance with AD 81-15-04 R1. The
actions specified by the proposed AD are intended to prevent failure of
the horizontal stabilizer rear spar caused by cracks at the elevator
outboard hinge attachment, which could result in loss of control of the
airplane.
DATES: Comments must be received on or before November 20, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 97-CE-152-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106. Comments may be inspected at this
location between 8 a.m. and 4 p.m., Monday through Friday, holidays
excepted.
Service information that applies to the proposed AD may be obtained
from The New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive,
Vero Beach, Florida 32960. This information also may be examined at the
Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. William Herderich, Aerospace
Engineer, FAA, Atlanta Aircraft Certification Office, One Crown Center,
1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone:
(770) 703-6084; facsimile: (770) 703-6097.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 97-CE-152-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 97-CE-152-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
Airworthiness Directive (AD) 81-15-04 R1, Amendment 39-4200,
currently requires repetitively inspecting certain Piper Model PA-31,
PA-31-300, PA-31-325, PA-31-350, and PA-31P-350 airplanes for cracks in
the horizontal stabilizer rear spar and the outboard hinge attach
bracket and, if cracks are found, incorporating Piper Stabilizer Rear
Spar Modification and Outboard Hinge Replacement Kit.
Actions Since Issuance of Previous Rule
Since the issuance of AD 81-15-04 R1, the FAA has received several
reports of cracks developing in the horizontal stabilizer rear spar and
the elevator outboard hinge attach brackets on airplanes that are in
compliance with this AD. The results of the investigation of these
reports show that the onset of cracks is believed to be caused by
improper fit of the hinge assembly in the spar channel and the method
of attaching the hinge bracket assembly to the rear spar.
Based on this new information, the manufacturer elected to redesign
the hinge bracket assembly and change the method of attaching the hinge
bracket assembly to the rear spar. This new design and change in the
attaching method should alleviate any further need for inspecting the
rear spar and hinge bracket assembly.
Relevant Service Information
Piper has issued Service Bulletin (SB) No. 1007, dated September
30, 1997, which specifies procedures for repetitively inspecting for
cracks in the elevator outboard hinge bracket and the horizontal
stabilizer rear spar. If cracks are found, the service information also
specifies following the instructions provided in Piper Kit No. 766-646
which is referenced in Piper SB No. 1007, dated September 30, 1997,
which provides procedures for modifying the rear spar and elevator
outboard hinge attachment by incorporating Piper Kit No. 766-646.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD action should be taken to prevent failure of the
horizontal stabilizer rear spar caused by cracks at the elevator
outboard hinge attachment, which could result in loss of control of the
airplane.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Piper Models PA-31, PA-31-300, PA-31-325, PA-
31-350, and PA-31P-350 airplanes of the same type design, the proposed
AD would supersede AD 81-15-04 R1 with a new AD that would require:
Inspecting the horizontal stabilizer rear spar at the
outboard hinge
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attachment and outboard hinge attach bracket for cracks,
If no cracks are found, the proposed AD would require
repetitively inspecting this area until cracks are found, and
If cracks are found or upon the accumulation of 500 hours
TIS, whichever occurs first, the proposed AD would require modifying
the horizontal stabilizer rear spar by incorporating Piper Kit No. 766-
646.
The incorporation of this kit would terminate the currently
required repetitive inspections. Accomplishment of the proposed
modification would be in accordance with the Instructions in Piper Kit
No. 766-646 which is referenced in Piper Service Bulletin No. 1007,
dated September 30, 1997.
Differences Between the Service Information and the Proposed AD
The compliance time specified in the Piper Service Bulletin No.
1007, dated September 30, 1997, is different than the compliance time
in the proposed AD. The FAA is not using the 50 hours time-in-service
(TIS) as the initial and repetitive inspection times, as specified in
the service bulletin. Fifty hours TIS or less is normally reserved for
urgent safety of flight conditions. The proposed AD is not considered
an urgent safety of flight condition, it is superseding an action that
already requires repetitive inspections. Based on engineering judgment
and the service history received from the field, the FAA is proposing
the initial and repetitive inspection time be increased to 100 hours
TIS in order to allow operators a reasonable amount of time to
accomplish the proposed action.
Cost Impact
The FAA estimates that 1,739 airplanes in the U.S. registry would
be affected by the proposed AD, that it would take approximately 11
workhours to per airplane to accomplish the proposed actions, and that
the average labor rate is approximately $60 an hour. Parts cost
approximately $478 per airplane. Based on these figures, the total cost
impact of the proposed AD on U.S. operators is estimated to be
$1,978,982, or $1,138 per airplane. This cost estimate does not take
into account the number of repetitive inspections that may be incurred
over the life of the airplane. These figures are based on the
presumption that no owner/operator of the affected aircraft has
accomplished this replacement.
Regulatory Impact
The regulations proposed herein would not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this 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, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 of the Federal Aviation Regulations 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. Section 39.13 is amended by removing Airworthiness Directive 81-
15-04 R1, Amendment 39-4200, and by adding a new AD to read as follows:
The New Piper Aircraft, Inc.: Docket No. 97-CE-152-AD; Supersedes AD
81-15-04 R1, Amendment 39-4200.
Applicability: The following airplane models and serial numbers,
certificated in any category:
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Models Serial Nos.
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PA-31, PA-31-300, and PA-31-325........... 31-2 through 31-8312019
PA-31-350................................. 31-5001 through 31-8553002
PA-31P-350................................ 31P-8414001 through 31P-
8414050
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Note 1: This AD applies to each airplane identified in the
preceding applicability provision, 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 (f) 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 the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: As indicated in the body of this AD, unless already
accomplished.
To prevent failure of the horizontal stabilizer rear spar caused
by cracks at the elevator outboard hinge attachment, which could
result in loss of control of the airplane:
(a) Within the next 100 hours time-in-service (TIS) after the
effective date of this AD, inspect the horizontal stabilizer rear
spar in the area of the outboard hinge attachment and the outboard
hinge attach bracket for cracks in accordance with the INSTRUCTIONS
section of Piper Service Bulletin (SB) No. 1007, dated September 30,
1997.
(b) If cracks are found, prior to further flight, modify the
horizontal stabilizer rear spar by incorporating Piper Kit No. 766-
646 in accordance with the INSTRUCTIONS contained in Piper Kit No.
766-646 which is referenced in Piper SB No. 1007, dated September
30, 1997.
(c) If no cracks are found, continue to inspect in accordance
with paragraph (a) of this AD at intervals not to exceed 100 hours
TIS. Upon the accumulation of 500 hours TIS after the effective date
of this AD or when cracks are found, whichever occurs first, modify
the horizontal stabilizer rear spar by incorporating Piper Kit No.
766-646 which is referenced in Piper SB No. 1007, dated September
30, 1997.
(d) Modifying the affected airplane by incorporating Piper Kit
No. 766-646 is considered a terminating action to the inspections
required in paragraphs (a) and (c) of this AD.
(e) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(f) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard,
suite 450, Atlanta, Georgia 30349.
(1) The request shall be forwarded through an appropriate FAA
Maintenance Inspector,
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who may add comments and then send it to the Manager, Atlanta ACO.
(2) Alternative methods of compliance approved in accordance
with AD 81-15-04 R1, are not considered approved as alternative
methods of compliance for this AD.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(g) All persons affected by this directive may obtain copies of
the documents referred to herein upon request to The New Piper
Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; or may
examine this document at the FAA, Central Region, Office of the
Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
(h) This amendment supersedes AD 81-15-04 R1, Amendment 39-4200.
Issued in Kansas City, Missouri, on September 14, 1998.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-25127 Filed 9-18-98; 8:45 am]
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