[Federal Register Volume 69, Number 78 (Thursday, April 22, 2004)]
[Proposed Rules]
[Pages 21768-21771]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-9105]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-CE-04-AD]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company 65, 90, 99, 
100, 200, 300, and 1900 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, 
300, and 1900 series airplanes. This proposed AD would require you to 
repetitively inspect the engine controls/cross shaft/pedestal for 
proper installation and torque, re-torque the cross shaft attach bolt, 
and modify the pedestal and replace the engine controls cross shaft 
hardware. Modification of the pedestal and replacement of the engine 
controls cross shaft hardware is terminating action for the repetitive 
inspection requirements. This proposed AD is the result of numerous 
reports of loose bolts on the pedestal attachment of the throttle/prop 
cross shaft assembly. We are issuing this proposed AD to detect and 
correct loose bolts not securing the pedestal cross shaft, which could 
result in limited effectiveness of the control levers. This failure 
could lead to an aborted takoff.

DATES: We must receive any comments on this proposed AD by June 22, 
2004.

ADDRESSES: Use one of the following to submit comments on this proposed 
AD:
     By mail: FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2004-CE-04-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106.
     By fax: (816) 329-3771.
     By e-mail: [email protected]. Comments sent 
electronically must contain ``Docket No. 2004-CE-04-AD'' in the subject 
line. If you send comments electronically as attached electronic files, 
the files must be formatted in Microsoft Word 97 for Windows or ASCII.
    You may get the service information identified in this proposed AD 
from Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140.
    You may view the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2004-CE-04-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. 
to 4 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Jeff Pretz, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4153; 
facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

How do I comment on this proposed AD?

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2004-CE-04-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it. We will date-stamp your postcard and 
mail it back to you.

Are there any specific portions of this proposed AD I should pay 
attention to?

    We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. If you 
contact us through a nonwritten communication and that contact relates 
to a substantive part of this proposed AD, we will summarize the 
contact and place the summary in the docket. We will consider all 
comments received by the closing date and may amend this proposed AD in 
light of those comments and contacts.

Discussion

What events have caused this proposed AD?

    The FAA has received numerous reports of loose bolts not securing 
the pedestal cross shaft on Raytheon Models B300, C90A, and 1900 series 
airplanes. Investigation revealed that the bolt securing the pedestal 
cross shaft can loosen in time and fall out. When the bolt backs out, 
the cross shaft will flex with throttle or propeller control 
application. This flexing of the cross shaft limits the effectiveness 
of the control levers and the operation of the landing gear warning, 
prop reverse not ready, autofeather, and ground idle micro switches (on 
models with switches at this location).

[[Page 21769]]

What is the potential impact if FAA took no action?

    This failure could limit the effectiveness of the engine control 
levers and result in an aborted takeoff due to failure to make takeoff 
power.

Is there service information that applies to this subject?

    Raytheon has issued Service Bulletin No. SB 73-3634, dated 
September 2003.

What are the provisions of this service information?

    The service bulletin includes procedures for:
    --Performing a recurring inspection of the engine controls/cross 
shaft/pedestal;
    --Re-torquing of the cross shaft attach bolt;
    --Modifying the pedestal; and
    --Replacing the engine controls cross shaft hardware.

FAA's Determination and Requirements of this Proposed AD

What has FAA decided?

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. Therefore, we are proposing AD action.

What would this proposed AD require?

    This proposed AD would require you to incorporate the actions in 
the previously-referenced service bulletin.

How does the revision to 14 CFR part 39 affect this proposed AD?

    On July 10, 2002, we published a new version of 14 CFR part 39 (67 
FR 47997, July 22, 2002), which governs FAA's AD system. This 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. This 
material previously was included in each individual AD. Since this 
material is included in 14 CFR part 39, we will not include it in 
future AD actions.

Costs of Compliance

How many airplanes would this proposed AD impact?

    We estimate that this proposed AD affects 5,025 airplanes in the 
U.S. registry.

What would be the cost impact of this proposed AD on owners/operators 
of the affected airplanes?

    We estimate the following costs to accomplish this proposed 
inspection and re-torque of the cross attach bolt:

----------------------------------------------------------------------------------------------------------------
                                                                      Total cost per      Total cost on U.S.
               Labor cost                         Parts cost             airplane              operators
----------------------------------------------------------------------------------------------------------------
1 workhour X $65 per hour = $65.........  Not Applicable............             $65  $65 X 5,025 = $326,625
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do the proposed modification of 
the pedestal and replacement of the engine controls cross shaft 
hardware:

----------------------------------------------------------------------------------------------------------------
                                                                Total cost per
                  Labor cost                      Parts cost       airplane       Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
2 workhours X $65 per hour = $130.............             $10            $140  $140 X 5,025 = $703,500
----------------------------------------------------------------------------------------------------------------

Regulatory Findings

Would this proposed AD impact various entities?

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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.

Would this proposed AD involve a significant rule or regulatory action?

    For the reasons discussed above, I certify that this proposed AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a summary of the costs to comply with this proposed AD 
and placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2004-CE-04-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Raytheon Aircraft Company: Docket No. 2004-CE-04-AD.

When Is the Last Date I Can Submit Comments on This Proposed AD?

    (a) We must receive comments on this proposed airworthiness 
directive (AD) by June 22, 2004.

What Other ADs Are Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
                 Model                            Serial Numbers
------------------------------------------------------------------------
(1) 65-A90, B90, C90, and C90A.........  LJ-76, LJ-114 through LJ-1691.
(2) E90................................  LW-1 through LW-347.

[[Page 21770]]

 
(3) F90................................  LA-2 through LA-236.
(4) 99, 99A, A99A, B99 and C99.........  U-1 through U-239.
(5) 100 and A100.......................  B-1 through B-94, B-100 through
                                          B-204, and B-206 through B-
                                          247.
(6) B100...............................  BE-1 through BE-137.
(7) 200 and B200.......................  BB-2, BB-6 through BB-185, BB-
                                          187 through BB-202, BB-204
                                          through BB-269, BB-271 through
                                          BB-407, BB-409 through BB-468,
                                          BB-470 through BB-488, BB-490
                                          through BB-509, BB-511 through
                                          BB-529, BB-531 through BB-550,
                                          BB-552 through BB-562, BB-564
                                          through BB-572, BB-574 through
                                          BB-590, BB-592 through BB-608,
                                          BB-610 through BB-626, BB-628
                                          through BB-646, BB-648 through
                                          BB-664, BB-666 through BB-694,
                                          BB-696 through BB-797, BB-799
                                          through BB-822, BB-824 through
                                          BB-870, BB-872 through BB-894,
                                          BB-896 through BB-990, BB-992
                                          through BB-1051, BB-1053
                                          through BB-1092, BB-1094, BB-
                                          1095, BB-1099 through BB-1104,
                                          BB-1106 through BB-1116, BB-
                                          1118 through BB-1184, BB-1186
                                          through BB-1263, BB-1265
                                          through BB-1288, BB-1290
                                          through BB-1300, BB-1302
                                          through BB-1313, BB-1315
                                          through BB-1384, BB-1389
                                          through BB-1425, BB-1427
                                          through BB-1447, BB-1449, BB-
                                          1450, BB-1452, BB-1453, BB-
                                          1455, BB-1456, BB-1458 through
                                          BB-1683, BB-1685 through BB-
                                          1716, BB-1718 through BB-1720,
                                          BB-1722, BB-1723, BB-1725, BB-
                                          1726, BB-1728 through BB-1826.
(8) 200C and B200C.....................  BL-1 through BL-23, BL-25
                                          through BL-57, BL-61 through
                                          BL-72, and BL-124 through BL-
                                          147.
(9) 200CT and B200CT...................  BN-1 through BN-4.
(10) 200T and B200T....................  BT-1 through BT-38, and BB-
                                          1314.
(11) 300 and 300LW.....................  FA-1 through FA-230; and FF-1
                                          through FF-19.
(12) B300..............................  FL-1 through FL-379.
(13) B300C.............................  FM-1 through FM-10; and FN-1.
(14) 1900..............................  UA-3.
(15) 1900C.............................  UB-1 through UB-74 and UC-1
                                          through UC-174.
(16) 1900D.............................  UE-1 through UE-439.
(17) 65-A90-1 (U-21A or U-21G).........  LM-1 through LM-141.
(18) 65-A90-2 (RU-21B).................  LS-1 through LS-3.
(19) 65-A90-3 (U-21 Series)............  LT-1 and LT-2.
(20) 65-A90-4 (U-21 Series)............  LU-1 through LU-16.
(21) H90 (T-44A).......................  LL-1 through LL-61.
(22) A100-1 (U-21J)....................  BB-3 through BB-5.
(23) A100 (U-21F)......................  B-95 through B-99.
(24) A200 (C-12A and C-12C)............  BC-1 through BC-75 and BD-1
                                          through BD-30.
(25) A200C (UC-12B)....................  BJ-1 through BJ-66.
(26) A200CT (C-12D, FWC-12D, C-12F)....  BP-1, BP-7 through BP-11, BP-
                                          19, BP-22, and BP-24 through
                                          BP-63.
(27) A200CT (RC-12D, RC-12H)...........  GR-1 through GR-12, and GR-14
                                          through GR-19.
(28) A200CT (RC-12G)...................  FC-1 through FC-3.
(29) A200CT (RC-12K, RC-12P and RC-12Q)  FE-1 through FE-9, and FE-25
                                          through FE-36.
(30) B200C (C-12F).....................  BL-73 through BL-112, and BL-
                                          118 through BL-123; BP-64
                                          through BP-71.
(31) B200C (C-12R).....................  BW-1 through BW-29.
(32) B200C (UC-12M)....................  BV-1 through BV-10.
(33) B200C (UC-12F)....................  BU-1 through BU-10.
(34) 1900C (C-12J).....................  UD-1 through UD-6.
------------------------------------------------------------------------

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of numerous reports of loose bolts on 
the pedestal attachment of the throttle/prop cross shaft assembly. 
The actions specified in this AD are intended to detect and correct 
loose bolts not securing the pedestal cross shaft, which could 
result in limited effectiveness of the control levers. This failure 
could lead to an aborted takoff.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Inspection and torque:    Initially inspect     Follow Part I,
 (i) inspect the engine        within the next 50    Accomplishment
 controls/cross shaft/         hours time-in-        Instructions of
 pedestal for proper           service (TIS),        Raytheon Aircraft
 installation and torque;      unless already done   Company Mandatory
 and (ii) re-torque the        within the last 50    Service Bulletin
 cross attach bolt.            hours TIS, and        No. SB 73-3634,
                               thereafter at         dated September
                               intervals not to      2003. The
                               exceed 100 hours      applicable airplane
                               until the             maintenance manual
                               modification in       also addresses this
                               paragraph (e)(3) of   issue.
                               this AD is done.
-----------------------------

[[Page 21771]]

 
(2) If any improper           Before further        Follow Part I,
 installation or wrong         flight after the      Accomplishment
 torque is found during any    inspection in which   Instructions of
 inspection required by        any improper          Raytheon Aircraft
 paragraph (e)(1) of this      installation or       Company Mandatory
 AD, correct the               wrong torque is       Service Bulletin
 installation or torque.       found.                No. SB 73-3634,
                                                     dated September
                                                     2003. The
                                                     applicable airplane
                                                     maintenance manual
                                                     also addresses this
                                                     issue.
-----------------------------
(3) Modify the pedestal and   At the next           Follow Part II,
 replace the engine controls   scheduled             Accomplishment
 cross shaft hardware.         maintenance/          Instructions of
 Modification of the           inspection interval   Raytheon Aircraft
 pedestal and replacement of   or 12 calendar        Company Mandatory
 the engine controls cross     months after the      Service Bulletin
 shaft hardware is the         effective date of     No. SB 73-3634,
 terminating action for the    this AD, whichever    dated September
 repetitive inspection and     occurs later. You     2003. The
 re-torque requirements        may do this time as   applicable airplane
 specified in paragraph        terminating action    maintenance manual
 (e)(1) of this AD.            for the repetitive    also addresses this
                               inspection and re-    issue.
                               torque requirements.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Wichita Aircraft 
Certification Office (ACO), FAA. For information on any already 
approved alternative methods of compliance, contact Jeff Pretz, 
Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4153; 
facsimile: (316) 946-4107.

May I Get Copies of the Documents Referenced in this AD?

    (g) You may get copies of the documents referenced in this AD 
from Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 
67201-0085; telephone: (800) 429-5372 or (316) 676-3140. You may 
view these documents at FAA, Central Region, Office of the Regional 
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

    Issued in Kansas City, Missouri, on April 16, 2004.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-9105 Filed 4-21-04; 8:45 am]
BILLING CODE 4910-13-P