[Federal Register Volume 64, Number 27 (Wednesday, February 10, 1999)]
[Rules and Regulations]
[Pages 6512-6514]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-2904]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-66-AD; Amendment 39-11032; AD 99-04-08]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 
1900C, and 1900D airplanes. This AD requires 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. This 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 this AD are intended to prevent the 
main landing gear from failing to lock 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: Effective March 26, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 26, 1999.

ADDRESSES: Service information that applies to this 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 may 
also be examined at 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; 
or at the Office of the Federal Register, 800 North Capitol Street, NW, 
suite 700, Washington, DC.

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:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to certain Raytheon 
Models 1900, 1900C, and 1900D airplanes was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on October 16, 1998 
(63 FR 55560). The NPRM proposed to require inspecting the main landing 
gear hydraulic actuators to determine whether any Frisby Aerospace 
actuator, part number (P/N) 120114-380041-11 or P/N 114-380041-13, is 
installed, and reworking or replacing any of these Frisby Aerospace 
actuators. Accomplishment of the proposed inspection as specified in 
the NPRM would be in accordance with Raytheon Mandatory Service 
Bulletin SB.32-3141, Issued: January, 1998. Accomplishment of the 
proposed

[[Page 6513]]

removal and replacement as specified in the NPRM would be in accordance 
with the applicable maintenance manual. Accomplishment of the rework as 
specified in the NPRM would be in accordance with Frisby Aerospace 
Service Bulletin 1FA10043-0001, dated October 1997.
    The NPRM was 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 378 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 1 workhour per 
airplane to accomplish the inspection, and that the average labor rate 
is approximately $60 an hour. Based on these figures, the total cost 
impact of the inspection on U.S. operators is estimated to be $22,680, 
or $60 per airplane.
    If any of the affected airplanes have any of the affected Frisby 
Aerospace main landing gear hydraulic actuators installed, it will take 
approximately 5 workhours per actuator to accomplish the replacement 
and an additional 4 workhours per actuator to accomplish the rework. 
The average labor rate is approximately $60 per hour. Parts will cost 
$3,871 for each new actuator; $2,865 for each overhauled actuator; and 
$1,997 for each rework/upgrade kit. Based on these figures, the cost 
impact on those operators choosing the replacement of the main landing 
gear hydraulic actuators will be approximately $8,342 per airplane that 
will have two new actuators installed, or $6,330 per airplane that will 
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 will be approximately 
$5,074 per airplane. Raytheon will give warranty credit for a 
replacement actuator until January 2001.

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.
    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) 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 final evaluation prepared for this 
action is contained 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, Incorporation by 
reference, 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:

99-04-08  Raytheon Aircraft Company (Type Certificate No. A24CE 
formerly held by the Beech Aircraft Corporation): Amendment 39-
11032; 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 actuator    Inspection compliance time
------------------------------------------------------------------------
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.

[[Page 6514]]

 
6,000 hours TIS through 6,999 hours TIS...  Within the next 600 hours
                                             TIS after the effective
                                             date of this AD.
7,000 hours TIS through 7,999 hours TIS...  Within the next 500 hours
                                             TIS after the effective
                                             date of this AD.
8,000 hours TIS through 8,999 hours TIS...  Within the next 400 hours
                                             TIS after the effective
                                             date of this AD.
9,000 hours TIS through 9,999 hours TIS...  Within the next 300 hours
                                             TIS after the 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 failing to lock 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, part number (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 1FA10043-0001, 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 the Wichita ACO.

    (e) The inspection required by this AD shall be done in 
accordance with Raytheon Mandatory Service Bulletin SB.32-3141, 
Issued: January, 1998. The rework required by this AD shall be done 
in accordance with Frisby Aerospace Service Bulletin 1FA10043-0001, 
dated October 1997. This incorporation by reference was approved by 
the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from Raytheon 
Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. 
Copies may be inspected at the FAA, Central Region, Office of the 
Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri, or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.
    (f) This amendment becomes effective on March 26, 1999.

    Issued in Kansas City, Missouri, on February 2, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 99-2904 Filed 2-9-99; 8:45 am]
BILLING CODE 4910-13-U