[Federal Register Volume 63, Number 200 (Friday, October 16, 1998)]
[Proposed Rules]
[Pages 55560-55562]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-27761]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-66-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Models 1900, 
1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain Raytheon Aircraft Company Models 1900, 
1900C, and 1900D airplanes. The proposed AD would require inspecting 
the main landing gear hydraulic actuators to determine whether a 
certain Frisby Aerospace actuator is installed, and reworking or 
replacing any of these Frisby Aerospace actuators. The proposed AD is 
the result of reports of fatigue cracks in the end cap of main landing 
gear hydraulic actuators manufactured by Frisby Aerospace and installed 
on the affected airplanes. The actions specified by the proposed AD are 
intended to prevent the main landing gear from not locking down due to 
the hydraulic actuator cracking and separating, which could result in 
loss of control of the airplane during landing, taxi, or ground 
operations.

DATES: Comments must be received on or before December 17, 1998.


[[Page 55561]]


ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 98-CE-66-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106. Comments may be inspected at this location 
between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from the Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. This information 
also may be examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Paul C. DeVore, Aerospace 
Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport 
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 
946-4142; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 proposal 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. 98-CE-66-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Central Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 98-CE-66-AD, Room 1558, 601 E. 12th Street, Kansas 
City, Missouri 64106.

Discussion

    The FAA has received reports of fatigue cracks in the end cap of 
main landing gear hydraulic actuators manufactured by Frisby Aerospace 
and installed on certain Raytheon Models 1900, 1900C, and 1900D 
airplanes. These actuators, part number (P/N) 114-380041-11 and P/N 
114-380041-13, have a sharp internal corner in the machined-end cap. 
The repetitive loads that are experienced in this area cause these 
fatigue cracks to form inside the actuator.
    These fatigue cracks, if not detected and corrected in a timely 
manner, could continue to grow until the actuator separated and the 
main landing gear would not lock down. This would result in loss of 
control of the airplane during landing, taxi, or ground operations.

Relevant Service Information

    Raytheon has issued Mandatory Service Bulletin SB.32-3141, Issued: 
January, 1998, which specifies procedures for inspecting the main 
landing gear hydraulic actuators to determine whether any Frisby 
Aerospace P/N 114-380041-11 or P/N 114-380041-13 main landing gear 
hydraulic actuator is installed. This service bulletin also specifies 
removing and either replacing or reworking the above-referenced Frisby 
Aerospace main landing gear hydraulic actuators. The procedures for the 
removal and replacement are included in the applicable maintenance 
manual. The procedures for the rework are included in Frisby Aerospace 
Service Bulletin 1FA10043, dated October 1997.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that AD action should be taken to prevent the main landing 
gear from not locking down due to the hydraulic actuator cracking and 
separating, which could result in loss of control of the airplane 
during landing, taxi, or ground operations.

Explanation of the Provisions of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Raytheon Models 1900, 1900C, and 1900D 
airplanes of the same type design, the FAA is proposing AD action. The 
proposed AD would require inspecting the main landing gear hydraulic 
actuators to determine whether any Frisby Aerospace actuator, P/N 114-
380041-11 or P/N 114-380041-13, is installed, and reworking or 
replacing any of these Frisby Aerospace actuators.
    Accomplishment of the proposed inspection would be required in 
accordance with Raytheon Mandatory Service Bulletin SB.32-3141, Issued: 
January, 1998. Accomplishment of the proposed removal and replacement 
would be required in accordance with the applicable maintenance manual. 
Accomplishment of the proposed rework would be required in accordance 
with Frisby Aerospace Service Bulletin 1FA10043, dated October 1997.

Cost Impact

    The FAA estimates that 378 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 1 
workhour per airplane to accomplish the proposed inspection. Based on 
these figures, the total cost impact of the proposed inspection on U.S. 
operators is estimated to be $22,680, or $60 per airplane.
    If any of the affected airplanes would have any of the affected 
Frisby Aerospace main landing gear hydraulic actuators installed, it 
would take approximately 5 workhours per actuator to accomplish the 
proposed replacement and an additional 4 workhours per actuator to 
accomplish the proposed rework. The average labor rate is approximately 
$60 per hour. Parts would cost $3,871 for each new actuator; $2865 for 
each overhauled actuator; and $1,997 for each rework/upgrade kit. Based 
on these figures, the cost impact on those operators choosing the 
proposed replacement of the main landing gear hydraulic actuators would 
be approximately $8,342 per airplane that would have two new actuators 
installed, or $6,330 per airplane that would have two overhauled 
actuators installed; and the cost impact on those operators choosing to 
incorporate the main landing gear hydraulic actuator rework/upgrade kit 
on each actuator would be approximately $5,074 per airplane. Raytheon 
will give warranty credit for a replacement actuator until January 
2001.

Regulatory Impact

    The regulations proposed herein would 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

[[Page 55562]]

proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 
will not have a significant economic impact, positive or negative, on a 
substantial number of small entities under the criteria of the 
Regulatory Flexibility Act. A copy of the draft regulatory evaluation 
prepared for this action has been placed in the Rules Docket. A copy of 
it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Raytheon Aircraft Company (Type Certificate No. A24CE formerly held 
by the Beech Aircraft Corporation): Docket No. 98-CE-66-AD.

    Applicability: The following airplane models and serial numbers, 
certificated in any category:

------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
1900..................................  UA-2 and UA-3.
1900C.................................  UB-1 through UB-74, and UC-1
                                         through UC-174.
1900C (C-12J).........................  UD-1 through UD-6.
1900D.................................  UE-1 through UE-299.
------------------------------------------------------------------------

    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 (d) 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: Inspection required as indicated below, unless 
already accomplished; and replacement or rework, if required, would 
be prior to further flight after the inspection required in 
paragraph (a) of this AD, unless already accomplished:

------------------------------------------------------------------------
 Hours time-in-service (TIS)
   accumulated on the main
    landing gear hydraulic             Inspection compliance time
           actuator
------------------------------------------------------------------------
Less Than 6,000 hours TIS....  Upon accumulating 6,600 hours TIS on the
                                actuator or within the next 600 hours
                                TIS after the effective date of this AD,
                                whichever occurs later.
6,000 hours TIS through 6,999  Within the next 600 hours TIS after the
 hours TIS.                     effective date of this AD.
7,000 hours TIS through 7,999   Within the next 500 hours TIS after the
 hours TIS.                     effective date of this AD.
8,000 hours TIS through 8,999  Within the next 400 hours TIS after the
 hours TIS.                     effective date of this AD.
9,000 hours TIS through 9,999  Within the next 300 hours TIS after the
 hours TIS.                     effective date of this AD.
10,000 Hours TIS or more.....  Within the next 200 Hours TIS after the
                                effective date of this AD.
------------------------------------------------------------------------

    To prevent the main landing gear from not locking down due to 
the hydraulic actuator cracking and separating, which could result 
in loss of control of the airplane during landing, taxi, or ground 
operations, accomplish the following:
    (a) Inspect the main landing gear hydraulic actuators to 
determine whether any Frisby Aerospace actuator, P/N 114-380041-11 
or P/N 114-380041-13, is installed. Accomplish this inspection in 
accordance with Raytheon Mandatory Service Bulletin SB.32-3141, 
Issued: January, 1998.
    (b) If any Frisby Aerospace actuator, P/N 114-380041-11 or P/N 
114-380041-13, is installed, prior to further flight, remove it and 
accomplish one of the following:
    (1) Replace the Frisby Aerospace actuator with one of a part 
number listed in the Material Information section of Raytheon 
Mandatory Service Bulletin SB.32-3141, Issued: January, 1998. 
Accomplish this replacement in accordance with the applicable 
maintenance manual; or
    (2) Rework the Frisby Aerospace actuator by incorporating the 
kit referenced in the Material Information section of Raytheon 
Mandatory Service Bulletin SB.32-3141, Issued: January, 1998. 
Accomplish this rework in accordance with Frisby Aerospace Service 
Bulletin 1FA10043, dated October 1997.
    (c) 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.
    (d) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from Wichita ACO.

    (e) All persons affected by this directive may obtain copies of 
the documents referred to herein upon request to the Raytheon 
Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; or 
may examine this document at the FAA, Central Region, Office of the 
Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri 64106.

    Issued in Kansas City, Missouri, on October 8, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-27761 Filed 10-15-98; 8:45 am]
BILLING CODE 4910-13-U