[Federal Register Volume 59, Number 21 (Tuesday, February 1, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-2090]
[[Page Unknown]]
[Federal Register: February 1, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-CE-60-AD]
Airworthiness Directives: Piper Aircraft Corporation PA24, PA30,
and PA39 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede AD 74-13-01, which
currently requires inspecting (one-time) the stabilator torque tube
bearing support fittings for looseness on certain Piper Aircraft
Corporation (Piper) PA24, PA30, and PA39 series airplanes, and, if
looseness is found, incorporating Piper Kit No. 760 835 (Hi-Shear Rivet
Replacement). The proposed action would retain the initial inspection
of the stabilator torque tube bearing support fittings, and would make
these inspections repetitive unless the above referenced service kit is
incorporated on all four stabilator torque tube bearing support
fittings. Incidents of looseness of the stabilator torque tube bearing
support fittings on several of the affected airplanes in compliance
with the current AD prompted this action. The actions specified by the
proposed AD are intended to prevent loss of pitch control because of
looseness of the stabilator torque tube bearing support fittings, which
could result in loss of control of the airplane.
DATES: Comments must be received on or before April 8, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 93-CE-60-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 Piper Aircraft Corporation, 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: Christina Marsh, Aerospace Engineer,
FAA, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, suite
210C, Atlanta, Georgia 30349; telephone (404) 991-2910; facsimile (404)
991-3606.
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. 93-CE-60-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 Assistant Chief Counsel,
Attention: Rules Docket No. 93-CE-60-AD, room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
AD 74-13-01, Amendment 39-1870, currently requires inspecting (one-
time) the stabilator torque tube bearing support fittings for looseness
on Piper PA24, PA30, and PA39 series airplanes, and, if looseness is
found, incorporating Piper Kit No. 760 835 (Hi-Shear Rivet
Replacement).
The FAA has received reports of incidents where looseness of the
stabilator torque tube bearing support fittings was discovered on
several Piper PA24, PA30, and PA39 airplanes. All of these airplanes
were in compliance with the one-time inspection requirement of AD 74-
13-01, but did not have Piper Kit No. 760 835 (Hi-Shear Rivet
Replacement) incorporated on all four stabilator torque tube bearing
support fittings.
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that (1) The one-time inspection of the stabilator torque
tube bearing support fittings on the referenced airplanes that is
currently required by AD 74-13-01 should be accomplished repetitively
unless Piper Kit No. 760 835 (Hi-Shear Rivet Replacement) is
incorporated on all four stabilator torque tube bearing support
fittings; and (2) AD action should be taken to prevent loss of pitch
control because of looseness of the stabilator torque tube bearing
support fittings, which could result in loss of control of the
airplane.
Since an unsafe condition has been identified that is likely to
exist or develop in other Piper PA24, PA30, and PA39 series airplanes
of the same type design that have not incorporated Piper Kit No. 760
835 (Hi-Shear Rivet Replacement) on all four stabilator torque tube
bearing support fittings, the proposed AD would supersede AD 74-13-01
with a new AD that would retain the initial inspection of the
stabilator torque tube bearing support fittings, and would make these
inspections repetitive unless the above referenced service kit is
incorporated on all four stabilator torque tube bearing support
fittings.
The FAA estimates that 4,409 airplanes in the U.S. registry would
be affected by the proposed AD, that it would take approximately 1
workhour per airplane to accomplish the proposed initial inspection,
and that the average labor rate is approximately $55 an hour. Based on
these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $242,495. This figure does not account for
any repetitive inspections that would be required by the proposed AD.
However, incorporating Piper Kit No. 760 835 (Hi-Shear Rivet
Replacement) on all four stabilator torque tube bearing support
fittings eliminates the need for the repetitive inspection requirement
of this AD. In addition, this kit may have been incorporated through
compliance with AD 75-27-08, Amendment 39-2624. This AD requires
inspecting the rivets of the stabilator torque tube bearing support
fittings, and the modification for any misaligned rivets is the
incorporation of the referenced kit. The cost figure presented above is
based on the assumption that none of the owners/operators that would be
affected by the proposed AD have incorporated Piper Kit No. 760 835.
The FAA anticipates that numerous owners/operators have incorporated
this kit, thereby reducing the cost impact of the proposed action.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing AD 74-13-01, Amendment 39-
1870, and by adding the following new airworthiness directive to read
as follows:
Piper Aircraft Corporation: Docket No. 93-CE-60-AD; Supersedes AD
74-13-01, Amendment 39-1870.
Applicability: The following model and serial number airplanes,
certificated in any category, that have not incorporated Piper Kit
No. 760 835 (Hi-Shear Rivet Replacement) on all four stabilator
torque tube bearing support fittings:
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Model Serial Nos.
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PA24-180, PA24-250 and PA24-260.. 24-1 through 24-5047.
PA24-400......................... 26-2 through 26-148.
PA30............................. 30-1 through 30-2000.
PA39............................. 39-1 through 39-155.
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Note 1: Piper Kit No. 760 835 (Hi-Shear Rivet Replacement), may
have been incorporated through compliance with AD 75-27-08,
Amendment 39-2624. This AD requires inspecting the rivets of the
stabilator torque tube bearing support fittings, and the
modification for any misaligned rivets is the incorporation of the
referenced kit. Airplanes incorporating this kit on all four
stabilator torque tube bearing support fittings are not affected by
this AD.
Compliance: Required within the next 100 hour time-in-service
(TIS) after the effective date of this AD, unless already
accomplished, and thereafter as indicated.
To prevent loss of pitch control because of looseness of the
stabilator torque tube bearing support fittings, which could result
in loss of control of the airplane, accomplish the following:
(a) Inspect the stabilator torque tube bearing support fittings
for looseness by accomplishing the following:
(1) Remove the tail cone and right rear aft fuselage access
door.
(2) Grasp the stabilator tip and shake the tip from left to
right and up and down.
Note 2: Piper Service Bulletin 411A, dated April 10, 1974,
specifies these same procedures for inspecting the stabilator torque
tube bearing support fittings.
(b) If looseness is found during the inspection specified in
paragraph (a) of this AD, prior to further flight, incorporate Piper
Kit No. 760 835 (Hi-Shear Rivet Replacement) on the affected
fitting, and reinstall the tail cone and right rear aft fuselage
access door.
(c) If looseness is not found during the inspection specified in
paragraph (a) of this AD, prior to further flight, reinstall the
tail cone and right rear aft fuselage access door, and reinspect the
stabilator torque tube bearing support fittings for looseness at
intervals not to exceed 100 hours TIS until Piper Kit No. 760 835
(Hi-Shear Rivet Replacement) is incorporated on all four stabilator
torque tube bearing support fittings.
(d) Incorporating Piper Kit No. 760 835 (Hi-Shear Rivet
Replacement) on all four stabilator torque tube bearing support
fittings is considered terminating action for the inspection
requirement of this AD.
(e) Special flight permits may be issued in accordance with FAR
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
compliance time that provides an equivalent level of safety may be
approved by the Manager, Atlanta Aircraft Certification Office
(ACO), 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The
request shall be forwarded through an appropriate FAA Maintenance
Inspector, who may add comments and then send it to the Manager,
Atlanta ACO.
Note 3: 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 document referred to herein upon request to the Piper Aircraft
Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or may
examine this document at the FAA, Central Region, Office of the
Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
(h) This amendment supersedes AD 74-13-01, Amendment 39-1870.
Issued in Kansas City, Missouri, on January 24, 1994.
Bobby W. Sexton,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-2090 Filed 1-31-94; 8:45 am]
BILLING CODE 4910-13-U
