[Federal Register Volume 60, Number 61 (Thursday, March 30, 1995)]
[Rules and Regulations]
[Pages 16366-16367]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-7784]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-CE-15-AD; Amendment 39-9184; AD 95-02-17]


Airworthiness Directives; Beech Aircraft Corporation Model 1900D 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 95-02-17, which was sent 
previously to known U.S. owners and operators of certain Beech Aircraft 
Corporation Model 1900D airplanes. This AD requires inspecting (one-
time) the elevator trim tab control cables at the top of the vertical 
stabilizer to ensure that cables (at the left, right, and crossover 
pulleys) are correctly routed around the pulleys, within the cable 
guide pins, and are not contacting any structure; and replacing any 
cable that is incorrectly routed or chafed. The actions specified by 
this AD are intended to prevent in-flight separation of the elevator 
trim tab control cable caused by misrouting, which could result in loss 
of control of the airplane.

DATES: Effective April 17, 1995, to all persons except those to whom it 
was made immediately effective by priority letter AD 95-02-17, issued 
January 25, 1995, which contained the requirements of this amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before June 16, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket 95-CE-15-AD, Room 1558, 601 E. 12th 
Street, Kansas City, Missouri 64106.
    Information that relates to this AD may be examined at the Rules 
Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Steven E. Potter, Wichita Aircraft 
Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, 
Wichita, Kansas 67209; telephone (316) 946-4124; facsimile (316) 946-
4407.

SUPPLEMENTARY INFORMATION: The FAA has received a report of an in-
flight separation of the elevator trim tab control (``nose up'' and 
``nose down'') cable on a Beech Model 1900D airplane. The reported 
cable separation prevented the airplane flight crew from using manual 
and electrical nose up trim, and the flight crew experienced high 
elevator ``nose down'' control forces. The flight crew was then able to 
land the airplane without further incident.
    Investigation of this incident showed that the elevator trim tab 
control cable had separated in the vicinity of its guide pulley, which 
is located at the top of the vertical stabilizer. The cable had been 
routed outside the lower cable pulley guard pin instead of under the 
guard pin. The routing configuration caused the cable to rub against 
the stabilizer rib, resulting in cable separation.
    Since an unsafe condition has been identified that is likely to 
exist or develop in other Beech Model 1900D airplanes of the same type 
design, the FAA issued priority letter AD 95-02-17 on January 25, 1995, 
to prevent in-flight separation of the elevator trim tab control cable 
caused by misrouting, which could result in loss of control of the 
airplane. The AD requires inspecting (one-time) the elevator trim tab 
control cables at the top of the vertical stabilizer to ensure that 
cables (at the left, right, and crossover pulleys) are correctly routed 
around the pulleys, within the cable guide pins, and are not contacting 
any structure; and replacing any cable that is incorrectly routed or 
chafed. Accomplishment of the required actions is in accordance with 
the Beech 1900D Maintenance Manual, part number 129-590000-15A11, 
Chapters 5-20-07, page 203; 6-40-00, page 3; 6-50-00, page 16; and 27-
30-04, pages 202 and 203.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make AD 95-02-17 effective immediately by individual letters 
issued on January 25, 1995, to known U.S. operators of certain Beech 
Model 1900D airplanes. These conditions still exist, and the AD is 
hereby published in the Federal Register as an amendment to section 
39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it 
effective as to all persons.

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. 95-CE-15-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 that 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 [[Page 16367]] and placed in the Rules Docket. A copy of 
it, if filed, may be obtained from 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.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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. 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 adding a new airworthiness directive 
to read as follows:

95-02-17 Beech Aircraft Corporation: Amendment 39-9184; Docket No. 
95-CE-15-AD.

    Applicability: Model 1900D airplanes, serial numbers UE-1 
through UE-131, certificated in any category.

    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 use the authority 
provided in paragraph (c) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition, or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any aircraft from the applicability of this AD.

    Compliance: Required prior to further flight after the effective 
date of this AD, unless already accomplished.
    To prevent in-flight separation of the elevator trim tab control 
cable, which could lead to loss of control of the airplane, 
accomplish the following:
    (a) In accordance with Beech 1900D Maintenance Manual, part 
number 129-590000-15A11, Chapters 5-20-07, page 203; 6-40-00, page 
3; 6-50-00, page 16; and 27-30-04, pages 202 and 203:
    (1) Remove access panel Number 333ATC, which is located on the 
top surface of the horizontal stabilizer, to gain access to the 
elevator trim tab cable, guides, and pulleys;
    (2) Inspect the cable routing to ensure that cables (at the 
left, right, and crossover pulleys) are correctly routed around the 
pulleys, within the cable guide pins, and are not contacting any 
structure; and
    (3) Replace any cable that is incorrectly routed (cable that 
does not meet the criteria above in paragraph (a)(2) of this AD) or 
is chafed.

    Note 2: The procedures listed in Beech Communique 1900D-112, 
dated January 1995, ``Inspection of Elevator Trim Tab Control 
Cables'', are similar to those included in this priority letter AD. 
Complying with all procedures in Beech Communique 1900D-112 is 
considered equivalent to the requirements of paragraphs (a)(1), 
(a)(2), and (a)(3) of this AD, and is considered ``unless already 
accomplished'' for this portion of the AD.

    Note 3: The compliance time specified in this AD takes 
precedence over that specified in Beech Communique 1900D-112, dated 
January 1995, ``Inspection of Elevator Trim Tab Control Cables''.

    (b) 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.
    (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, Wichita Aircraft Certification Office 
(ACO), FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, 
Kansas 67209. The request shall be forwarded through an appropriate 
FAA Maintenance Inspector, who may add comments and then send it to 
the Manager, Wichita ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

    (d) Information that relates 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 (39-9184) becomes effective on April 17, 
1995, to all persons except those persons to whom it was made 
immediately effective by priority letter AD 95-02-17, issued January 
25, 1995, which contained the requirements of this amendment.

    Issued in Kansas City, Missouri, on March 24, 1995.
Dwight A. Young,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-7784 Filed 3-29-95; 8:45 am]
BILLING CODE 4910-13-U