[Federal Register Volume 64, Number 95 (Tuesday, May 18, 1999)]
[Rules and Regulations]
[Pages 26837-26839]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-12295]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-18-AD; Amendment 39-11171; AD 99-10-07]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Corporation Beech 
Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, 
C90A, E90, H90, and F90 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) 99-10-07, which was sent 
previously to all known U.S. owners and operators of Raytheon Aircraft 
Corporation (Raytheon) Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 
65-A90-3, 65-A90-4, B90, C90, C90A, E90, H90, and F90 airplanes. This 
AD requires inspecting for interference or damage between the elevator 
control cable and equipment under the cockpit floor panels (wire 
harnesses, stainless steel clamps, etc.) and running a cloth wrap 
around the control cable to detect broken strands of the control cable. 
This AD also requires replacing or repairing any damaged items, 
securing any component that is interfering with the elevator control 
cable, and installing additional supports and clamps as necessary to 
prevent sagging or further interference. This AD resulted from reports 
of reduced or loss of elevator control on five of the affected 
airplanes. The actions specified by this AD are intended to detect and 
correct interference between the elevator control cable and equipment 
under the cockpit floor panels before the elevator control cable 
breaks, which could result in loss of elevator control with potential 
loss of control of the airplane.

DATES: Effective June 8, 1999, to all persons except those to whom it 
was made immediately effective by priority letter AD 99-10-07, issued 
May 3, 1999, which contained the requirements of this amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before July 6, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket 99-CE-18-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.
    Information related to this AD may be examined at the Rules Docket 
at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Todd Dixon, Aerospace Engineer, 
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 
100, Mid-Continent Airport, Wichita, Kansas 67209, telephone: (316) 
946-4152; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

    On May 3, 1999, the FAA issued priority letter AD 99-10-07, which 
applies to all Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-
3, 65-A90-4, B90, C90, C90A, E90, H90, and F90 airplanes. That AD 
resulted from reports of reduced or loss of elevator control on 
Raytheon Beech 90 series airplanes. The following briefly describes 
these incidents:

--During flight on a Raytheon Beech Model E90 airplane, the pilot 
realized he could only utilize elevator up control, declared an 
emergency, and safely landed using engine power and trim. Investigation 
revealed that the down elevator cable was severed due to chafing 
between this cable and the windshield de-ice circuit electrical wire. 
Verbal communication with an FAA Flight Standards employee indicated 
another incident of loss of elevator control due to interference with 
electrical wiring on a Raytheon Beech 90 series airplane; and
--The elevator down cable separated on a Raytheon Beech Model E90 
airplane because of interference between this cable and the stainless 
steel clamp that joined two bleed air supply ducts. The FAA has 
received reports of two other incidents of reduced/loss of elevator 
control due to interference between the elevator down cable and the 
bleed air ducts on Raytheon Beech 90 series airplanes.

    Priority letter AD 99-10-07 requires the following on the above-
referenced airplanes:

--Removing the pilot's seat and floor panels in the cockpit area on the 
pilot's side of the airplane and inspecting the entire area for 
interference or damage between the elevator control cable and equipment 
under the cockpit floor panels (wire harnesses, stainless steel clamps, 
etc.);
--Running a cloth wrap around the control cable to detect broken 
strands of the control cable (Ref: 90 Series Maintenance Manual, 
Sections 5-20-00, 5-20-01 (if applicable), and 20-04-00);

[[Page 26838]]

--Replacing or repairing any damaged items found during the required 
inspection and cloth wrap procedure. This would include chafing damage 
and nicks, cuts, and broken strands on the control cable (Ref: 90 
Series Maintenance Manual, Section 20-04-00, for criteria to determine 
if the cable needs to be replaced);
--Securing any component that is interfering with the elevator control 
cable and installing additional supports and clamps as necessary to 
prevent sagging or further interference between the elevator control 
cable and equipment under the cockpit floor panels. Use best shop 
practices and Advisory Circular (AC) 43.13-1B as guides for installing 
the additional supports;
--reinspecting the elevator control cable upon completion of any rework 
or replacement to assure that there is no interference; and
--reinstalling the floor panels and the pilot's seat.

The FAA's Determination and Explanation of the AD

    Since an unsafe condition was identified that is likely to exist or 
develop in other Raytheon Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-
2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, H90, and F90 airplanes of 
the same type design airplanes, the FAA:
    1. Determined that the elevator control cable on the Raytheon Beech 
90 series airplanes could interfere with wire harnesses, stainless 
steel clamps, and other equipment under the cockpit floor panels;
    2. Determined that immediate AD action should be taken to detect 
and correct such interference before the elevator control cable breaks, 
which could result in loss of elevator control with potential loss of 
control of the airplane; and
    3. Issued AD 99-10-07 as a priority letter on May 3, 1999.

Compliance Time of This AD

    The compliance time of this AD is structured such that the required 
actions would occur at the same time as the first Phase III inspection 
(at 600 hours time-in-service (TIS)) for low-time airplanes with less 
than 600 hours TIS or within the next 10 hours TIS for those airplanes 
with over 590 hours total TIS. The Phase III inspection is the first 
time the pilot's seat and the floor panels are removed during regular 
maintenance.
    Recent inspections of low-time airplanes and airplanes just off the 
assembly line have not revealed any of the interference problems 
referenced in this document. By structuring the compliance time to 
coincide with the Phase III inspection, operators of low-time airplanes 
do not have to accomplish an unnecessary or unjustified inspection.

Determination of the Effective Date of the AD

    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 the AD effective immediately by individual letters 
issued on May 3, 1999, to all known U.S. operators of Beech Models 65-
90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, 
E90, H90, and F90 airplanes. These conditions still exist, and the AD 
is hereby published in the Federal Register as an amendment to 
Sec. 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 rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 99-CE-18-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    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 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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

99-10-07  Raytheon Aircraft Corporation: Amendment 39-11171; Docket 
No. 99-CE-18-AD.

    Applicability: Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 
65-A90-3, 65-A90-4, B90, C90, C90A, E90, H90, and F90 airplanes, all 
serial numbers, certificated in any category:


[[Page 26839]]


    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 (c) 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: Required as indicated in the body of this AD, unless 
already accomplished.
    To detect and correct interference between the elevator control 
cable and equipment under the cockpit floor panels before the 
elevator control cable breaks, which could result in loss of 
elevator control with potential loss of control of the airplane, 
accomplish the following:
    (a) Upon accumulating 600 hours total time in service (TIS) on 
the airplane or within the next 10 hours TIS after the effective 
date of this AD, whichever occurs later, accomplish the following:
    (1) Remove the pilot's seat and floor panels in the cockpit area 
on the pilot's side of the airplane and inspect the entire area for 
interference or damage between the elevator control cable and 
equipment under the cockpit floor panels (wire harnesses, stainless 
steel clamps, etc.); and
    (2) Run a cloth wrap around the control cable to detect broken 
strands of the control cable (Ref: 90 Series Maintenance Manual, 
Sections 5-20-00, 5-20-01 (if applicable), and 20-04-00).
    (b) Prior to further flight after the actions required by 
paragraph (a), including all subparagraphs, of this AD, accomplish 
the following:
    (1) Replace or repair any damaged items found during the 
inspection and cloth wrap procedure required in paragraphs (a)(1) 
and (a)(2) of this AD, respectively. This would include chafing 
damage and nicks, cuts, and broken strands on the control cable 
(Ref: 90 Series Maintenance Manual, Section 20-04-00, for criteria 
to determine if the cable needs to be replaced);
    (2) Secure any component that is interfering with the elevator 
control cable and install additional supports and clamps as 
necessary to prevent sagging or further interference between the 
elevator control cables and equipment under the cockpit floor 
panels. Use best shop practices and Advisory Circular (AC) 43.13-1B 
as guides for installing the additional supports;
    (3) Reinspect the elevator control cables in accordance with the 
procedures specified in paragraph (a)(1) of this AD upon completion 
of any rework or replacement to assure that there is no 
interference; and
    (4) Re-install the floor panels and pilot's seat.

    Note 2: Raytheon Safety Communique No. 143, dated October 1997, 
is not considered an alternative method of compliance to this AD.

    (c) An alternative method of compliance or adjustment of the 
compliance times that provides an equivalent level of safety may be 
approved by the Manager, Wichita Aircraft Certification Office 
(ACO), 1801 Airport Road, Room 100, 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

    (d) Information related to this priority letter AD may be 
examined at the FAA, Central Region, Office of the Regional Counsel, 
Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
    (e) This amendment becomes effective on June 8, 1999, to all 
persons except those persons to whom it was made immediately 
effective by priority letter AD 99-10-07, issued May 3, 1999, which 
contains the requirements of this amendment.

    Issued in Kansas City, Missouri, on May 7, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-12295 Filed 5-17-99; 8:45 am]
BILLING CODE 4910-13-U