[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: 94-2091]
[[Page Unknown]]
[Federal Register: February 1, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-CE-57-AD; Amendment 39-8810; AD 93-24-02 R1]
Airworthiness Directives: Piper Aircraft Corporation PA31, PA31P,
and PA31T Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment revises Airworthiness Directive (AD) 93-24-02,
which currently requires inspecting the elevator control tube assembly
area for damage (cracks, separation, corrosion, wear, elongated holes,
etc.) on Piper Aircraft Corporation (Piper) PA31, PA31P, and PA31T
series airplanes, and replacing any damaged parts. An incident where
one of the affected airplanes experienced complete loss of elevator
control while in flight prompted that AD. Since issuance of that
action, the Federal Aviation Administration (FAA) has received reports
that the figure contained in the AD specifies an incorrect installation
of the elevator control tube assembly. This action maintains the
requirements of the previous AD, and corrects the figure to reflect the
correct installation. The actions specified by this AD are intended to
prevent elevator control problems caused by a damaged elevator control
tube assembly, which could result in loss of control of the airplane.
DATES: Effective February 15, 1994.
Comments for inclusion in the Rules Docket must be received on or
before March 31, 1994.
ADDRESSES: Submit comments in triplicate to the FAA, Central Region,
Office of the Assistant Chief Counsel, Attention: Rules Docket No. 93-
CE-57-AD, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
Information that relates to this AD may be examined at the FAA,
Central Region, Office of the Assistant Chief Counsel, Attention: Rules
Docket 93-CE-57-AD, room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
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: AD 93-24-02, Amendment 39-8751 (58 FR 63524,
December 2, 1993), currently requires inspecting the elevator control
tube assembly area for damage (cracks, separation, corrosion, wear,
etc.) on Piper PA31, PA31P, and PA31T series airplanes, and replacing
any damaged parts.
A report of an incident where a Piper PA31T series airplane
experienced a loss of elevator control while in flight prompted AD 93-
24-02. The pilot landed the airplane safely using the elevator trim
control. Investigation by the National Transportation Safety Board
(NTSB) and the FAA disclosed that the aft control rod end bearing, part
number (P/N) 49261-02, had separated into two pieces. This aft control
rod end bearing connects the elevator control tube to the elevator
horn. The elevator control was subsequently mechanically disconnected
from the pilot's control yoke and the elevator downspring. Further
investigation revealed a fatigue crack at the thread root, which
extended through the rod end cross section.
This incident prompted this operator to conduct an inspection of
the elevator control tube assembly area on all of the Piper PA31,
PA31P, and PA31T series airplanes in this particular operator's fleet.
The results were summarized in a Mechanical Reliability Report (MRR),
which was submitted to the FAA. This MRR specifies problems in the
elevator control tube assembly area on 21 of the 23 inspected
airplanes. The following briefly describes some of the discrepancies:
13 airplanes had incorrect push rod connecting bolts
installed in the forward or aft positions (or both);
12 airplanes had push rod connecting bolts with wear or
pitting corrosion (or both) in the shank area;
13 airplanes had excessive play in the aft rod end
bearings;
7 airplanes had aft rod ends with moderate to severe wear
or corrosion (or both) on the bearing ball; and
3 airplanes had binding in the rod ends, one of which was
completely frozen.
Since issuance of AD 93-24-02, the FAA has received several reports
that the figure contained in the AD specifies an incorrect installation
of the elevator control tube assembly area. In particular, the figure
depicts installation of the AN174-11A and AN174-12A bolts with a
castellated nut and cotter pin. This installation is actually
accomplished utilizing a MS20365-428C nut instead of a castellated nut
and cotter pin.
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD 93-24-02 should be revised in order to prevent
elevator control problems caused by a damaged elevator control tube
assembly.
Since an unsafe condition has been identified that is likely to
exist or develop in other Piper PA31, PA31P, and PA31T series airplanes
of the same type design, this AD revises AD 93-24-02 by (1) maintaining
the requirement of inspecting the elevator control tube assembly area
for damage, and replacing any damaged part; and (2) correcting the
Figure contained in the AD to include the correct installation of the
AN174-11A and AN174-12A bolts.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for public
prior comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting immediate flight safety and, thus, was not
preceded by notice and opportunity to comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 will be considered,
and this rule may be amended in light of the comments received. Factual
information that supports the commenter's ideas and suggestions is
extremely helpful in evaluating the effectiveness of the AD action and
determining whether additional rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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
AD 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-57-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation and must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket (otherwise, an evaluation is
not required). A copy of it, if filed, may be obtained from the Rules
Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 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 Amendment 39-8751 (58 FR
63524, December 2, 1993), and adding a new AD to read as follows:
93-24-02 R1 Piper Aircraft Corporation: Amendment 39-8810; Docket
No. 93-CE-57-AD.
Applicability: PA31, PA31P, and PA31T series airplanes (all
models and serial numbers), certificated in any category.
Compliance: Required within the next 30 hours time-in-service
after the effective date of this AD, unless already accomplished.
To prevent elevator control problems, which could lead to loss
of control of the airplane, accomplish the following:
(a) Ensure that the elevator control tube assembly area is not
damaged by accomplishing the following inspections and procedures:
(1) Gain access to the elevator controls in the tail by removing
the bottom half of the tailcone and the fuselage side panels.
(2) Remove the long pushrod that connects the bellcrank and the
elevator horn.
(3) Secure the aft end of the bungee link to the elevator horn
with safety wire for removal and installation of the bungee attach
bolt.
(4) Inspect, using FAA-approved magnetic procedures, the rod end
shank and threads for cracks. If found cracked, prior to further
flight, replace the rod end with part number (P/N) 49261-02 or P/N
452-658.
(5) Visually inspect the bearing in the rod end for wear and
free movement. If wear is found or the bearing will not move, prior
to further flight, replace the rod end with P/N 49261-02 or P/N 452-
658.
(6) Inspect, using a 10X magnifying glass, the forward attach
holes in the pushrod for cracks, corrosion, or elongation. If
cracks, corrosion, or elongation is found, prior to further flight,
replace the pushrod with P/N 40847-00, 40847-04, or 40847-07, as
applicable.
(7) Visually inspect the forward and aft attach area to ensure
that both a forward bolt, P/N 402 311 (AN 174-12A), and an aft bolt,
P/N 402 317 (AN 174-11A), are installed. If either one of these
bolts is not installed, prior to further flight, install the
applicable bolt or replace the existing bolt with one of the
applicable part number.
(8) Remove the safety wire, reinstall the pushrod, check to
ensure that the elevator rigging is correct, and reinstall the
bottom half of the tailcone and the fuselage side panels.
Note 1: Figure 1 of this AD illustrates the elevator assembly
and the specific areas that are to be inspected.
TR01FE94.014
(b) 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.
(c) 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: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(d) Information related to this AD may be examined at the FAA,
Central Region, Office of the Assistant Chief Counsel, Room 1558,
601 E. 12th Street, Kansas City, Missouri 64106.
(e) This amendment (39-8810) revises AD 93-24-02, Amendment 39-
8751.
(f) This amendment (39-8810) becomes effective on February 15,
1994.
Issued in Kansas City, Missouri, on January 24, 1994.
Bobby W. Sexton,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-2091 Filed 1-31-94; 8:45 am]
BILLING CODE 4910-13-U
