[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
