[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