[Federal Register Volume 67, Number 14 (Tuesday, January 22, 2002)]
[Rules and Regulations]
[Pages 2797-2799]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-1206]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-CE-80-AD; Amendment 39-12602; AD 2002-01-10]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company Beech Models 
65-90, 65-A90, 65-A90-1, 65-A90-4, B90, C90, C90A, E90, and H-90 
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) Beech Models 
65-90, 65-A90, 65-A90-1, 65-A90-4, B90, C90, C90A, E90, and H-90 
airplanes. This AD requires you to repetitively inspect the main 
landing gear upper torque knees and lower torque knees for evidence of 
fatigue cracks; and replace any torque knee with evidence of fatigue 
cracks. This AD is the result of reports of many incidents of main 
landing gear torque knees cracking or breaking on the above-referenced 
airplanes. The actions specified by this AD are intended to detect and 
replace cracked main landing gear torque knees, which could result in 
failure of the main landing gear and consequent loss of control of the 
airplane during takeoff, landing, or other ground operations.

DATES: This AD becomes effective on February 22, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
February 22, 2002.

ADDRESSES: You may get the service information referenced in this AD 
from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140; or on the Internet 
at http://www.raytheonaircraft.com/support/pubs/pdf/sb/32-3134r1.pdf> 
and 
http://www.raytheonaircraft.com/support/pubs/pdf/sb/32-3116.pdf>. These 
files are in Adobe Portable Document Format. The Acrobat Reader is 
available at http://www.adobe.com/>. You may view this information at 
the Federal Aviation Administration (FAA), Central Region, Office of 
the Regional Counsel, Attention: Rules Docket No. 99-CE-80-AD, 901 
Locust, Room 506, 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. Steven E. Potter, Aerospace 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4124; 
facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

    The FAA has received reports of many incidents of fatigue cracks 
occurring on main landing gear torque knees. There have been at least 
four reports where the main landing gear separated from the airplane.
    The cause of this problem is cumulative fatigue damage on the main 
landing gear torque knees.

What Is the Potential Impact if FAA Took No Action?

    This condition, if not corrected, could result in the failure of 
the main landing gear while the airplane is in operation with 
consequent loss of control of the airplane during takeoff, landing, or 
other ground operations.

Has FAA Taken Any Action to This Point?

    We issued 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 Beech Models 65-90, 65-A90, 65-A90-1, 65-A90-4, B90, 
C90, C90A, E90, and H-90 airplanes. This proposal was published in the 
Federal Register as a notice of proposed rulemaking (NPRM) on August 
27, 2001 (66 FR 44988). The NPRM proposed to require you to 
repetitively inspect the main landing gear upper torque knees and lower 
torque knees for evidence of fatigue cracks; and replace any torque 
knee with evidence of fatigue cracks.

Was the Public Invited to Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. We did not receive any comments on the proposed rule 
or on our determination of the cost to the public.

FAA's Determination

What is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:

--Provide the intent that was proposed in the NPRM for correcting the 
unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 2,124 airplanes in the U.S. 
registry.

What Is the Cost Impact of This AD on Owners/Operators of the Affected 
Airplanes?

    We estimate the following costs to inspect the landing gear torque 
knees:

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                                          Parts cost    Total cost
               Labor cost                per airplane  per airplane           Total cost U.S.  operators
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20 workhours  x  $60 per hour = $1200..          $50        $1,250   $1,250  x  2,124 = $2,655,000.
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[[Page 2798]]

    The manufacturer will allow warranty credit to the extent noted in 
the service bulletin.
    These costs only take into account the costs of the initial 
inspection. We have no way of determining the number of repetitive 
inspections each owner/operator will incur over the life of the 
affected airplane.
    We estimate the following costs to do any necessary torque knee 
replacements that would be required based on the results of the 
inspection. We have no way of determining the number of airplanes that 
may need such replacement:

----------------------------------------------------------------------------------------------------------------
                                                                                 Parts cost per   Total cost per
                                  Labor cost                                        airplane         airplane
----------------------------------------------------------------------------------------------------------------
8 workhours  x  $60 per hour = $480...........................................          $3,286           $3,766
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Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    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, under 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. FAA amends Sec. 39.13 by adding a new AD to read as follows:

2002-01-10  Raytheon Aircraft Company: Amendment 39-12602; Docket 
No. 99-CE-80-AD.

    (a) What airplanes are affected by this AD? This AD affects the 
following Beech airplane models and serial numbers that are 
certificated in any category:

------------------------------------------------------------------------
              Model                             Serial Nos.
------------------------------------------------------------------------
65-90, 65-A90, B90, C90, and C90A  LJ-1 through LJ-1559.
65-A90-1.........................  LM-1 through LM-141.
65-A90-4.........................  LU-1 through LU-16.
E90..............................  LW-1 through LW-347.
H-90.............................  LL-1 through LL-61.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the above airplanes must comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to detect and replace cracked main landing gear 
torque knees, which could result in failure of the main landing gear 
with consequent loss of control of the airplane during takeoff, 
landing, or other ground operations.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the main landing  Inspect within the    Do the action
 gear upper torque knee and    next 100 hours time-  following the
 lower torque knee for         in-service (TIS)      Accomplishment
 fatigue cracks.               after February 22,    Instructions
                               2002 (the effective   paragraph of
                               date of this AD),     Raytheon Aircraft
                               and thereafter at     Mandatory Service
                               intervals not to      Bulletin SB 32-
                               exceed 1,000 hours    3134, Revision 1,
                               TIS.                  Revised: July 1999,
                                                     and the applicable
                                                     airplane
                                                     maintenance manual.
(2) If fatigue cracks are     Before further        Do the action
 found in the main landing     flight after the      following the
 gear torque knees during      inspection.           Accomplishment
 any inspection required by                          Instructions
 this AD, replace the                                paragraph of
 cracked torque knees.                               Raytheon Aircraft
                                                     Recommended Service
                                                     Bulletin SB 32-
                                                     3116, Issued:
                                                     October 1999, and
                                                     the applicable
                                                     airplane model
                                                     maintenance manual.
(3) When both the left and    You may replace all   Do the action
 right main landing gear       torque knees at any   following the
 upper and lower torque        time, except for      Accomplishment
 knees are replaced with new   those torque knees    Instructions
 upper torque knees (part      that are found with   paragraph of
 number 50-810032-12) and      evidence of fatigue   Raytheon Aircraft
 new lower torque knees        cracks. Such torque   Recommended Service
 (part number 50-810295-25),   knees must be         Bulletin SB 32-
 the repetitive inspection     replaced before       3116, Issued:
 requirement of this AD is     further flight, as    October 1999, and
 no longer required.           required by           the applicable
                               paragraph (d)(2) of   airplane
                               this AD.              maintenance manual.
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Wichita Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Wichita ACO.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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

[[Page 2799]]

compliance in accordance with paragraph (e) 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Steven E. Potter, 
Aerospace Engineer, Wichita Aircraft Certification Office, FAA, 1801 
Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-
4124; facsimile: (316) 946-4407.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with Raytheon Mandatory Service Bulletin SB 32-3134, Revision 1, 
Revised: July 1999, and Raytheon Recommended Service Bulletin SB 32-
3116, Issued: October 1999. The Director of the Federal Register 
approved this incorporation by reference under 5 U.S.C. 552(a) and 1 
CFR part 51. You can get copies from Raytheon Aircraft Company, P.O. 
Box 85, Wichita, Kansas 67201-0085; or on the Internet at http://www.raytheonaircraft.com/support/pubs/pdf/sb/32-3134r1.pdf> and 
http://www.raytheonaircraft.com/support/pubs/pdf/sb/32-3116.pdf>. 
These files are in Adobe Portable Document Format. The Acrobat 
Reader is available at http://www.adobe.com/>. You can look at 
copies at the FAA, Central Region, Office of the Regional Counsel, 
901 Locust, Room 506, Kansas City, Missouri, or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on February 22, 2002.

    Issued in Kansas City, Missouri, on January 10, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-1206 Filed 1-18-02; 8:45 am]
BILLING CODE 4910-13-U