[Federal Register Volume 69, Number 161 (Friday, August 20, 2004)]
[Rules and Regulations]
[Pages 51549-51552]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-18923]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-CE-04-AD; Amendment 39-13774; AD 2004-17-02]
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: Final rule.

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

SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain 
Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, 300, and 
1900 series airplanes. This AD requires you to repetitively inspect the 
engine controls/cross shaft/pedestal for proper installation and 
torque, re-torque the cross shaft attach bolt, 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 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 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 takeoff.

DATES: This AD becomes effective on October 4, 2004.
    As of October 4, 2004, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: You may get the service information identified 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 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, Wichita, 
Kansas 67209; telephone: (316) 946-4153; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

    What events have caused this 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).
    The 65, 90, 99, 100, 200, 300, and 1900 Series airplanes all have a 
similar type design in the area affected by this AD.
    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.
    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 65, 90, 99, 100, 
200, 300, and 1900 series airplanes. This proposal was published in the 
Federal Register as a notice of proposed rulemaking (NPRM) on April 26, 
2004 (69 FR 22392). The NPRM proposed to require you to repetitively 
inspect the engine controls/cross shaft/pedestal for proper 
installation and torque, re-torque the cross shaft attach bolt, modify 
the pedestal, and replace the engine controls cross shaft hardware.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. The following 
presents the comment received on the proposal and FAA's response to the 
comment:

Comment Issue: The AD Is Not Needed

    What is the commenter's concern? The commenter is responsible for a 
large fleet (Models 99, 200, and 1900) of 62 airplanes that are 
affected by this AD. The fleet has accumulated more than 450,000 flight 
hours. The commenter states that the company has never experienced the 
problem in the fleet, and that regular inspection in the subject area 
and check of the subject bolts for tightness eliminates the problem. 
Therefore, the AD is not necessary.
    What is FAA's response to the concern? The FAA disagrees with the 
commenter's statement that, since the company has not experienced the 
problem in the fleet, that an AD is not necessary. The AD action was 
prompted by several reports of loose bolts not securing the pedestal 
cross shaft on Raytheon Models B300, C90A, and 1900 series airplanes. 
After issuance of a manufacturer's safety notice, FAA received more 
reports of loose bolts. Our decision to issue an AD action is based on 
reports from the field, the likelihood that the condition is likely to 
exist or develop on other products of this same type design, and the 
potential impact to

[[Page 51550]]

an aircraft with the subject condition if no action was taken.
    Therefore, to ensure that all affected airplanes do not have the 
unsafe condition, we are not changing the final rule AD action based on 
this comment.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for minor 
editorial corrections. We have determined that these minor corrections:

--Are consistent with 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.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the 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 does this AD impact? We estimate that this AD 
affects 5,025 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 do the 
inspection and re-torque of the cross attach bolt:

----------------------------------------------------------------------------------------------------------------
                                                           Total cost  per
            Labor cost                    Parts cost           airplane        Total cost  on U.S.  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 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

    Will this AD impact various entities? We have determined that this 
AD will not have federalism implications under Executive Order 13132. 
This AD 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.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
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]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2004-17-02 Raytheon Aircraft Company: Amendment 39-13774; Docket No. 
2004-CE-04-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on October 4, 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 Nos.
------------------------------------------------------------------------
(1) 65-A90, B90, C90, and C90A.........  LJ-76, LJ-114 through LJ-1691.
(2) E90................................  LW-1 through LW-347.
(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.

[[Page 51551]]

 
(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 takeoff.

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:......
    (i) inspect the engine
     controls/cross shaft/
     pedestal for proper
     installation and torque;
     and.
    (ii) re-torque the cross      Initially inspect   Follow Part I,
     attach bolt..                 within the next     Accomplishment
                                   50 hours time-in-   Instructions of
                                   service (TIS)       Raytheon Aircraft
                                   after October 4,    Company Mandatory
                                   2004 (the           Service Bulletin
                                   effective date of   No. SB 73-3634,
                                   this AD), unless    dated September
                                   already done        2003. The
                                   within the last     applicable
                                   50 hours TIS, and   airplane
                                   thereafter at       maintenance
                                   intervals not to    manual also
                                   exceed 100 hours    addresses this
                                   TIS until the       issue.
                                   modification in
                                   paragraph (e)(3)
                                   of this AD is
                                   done.

[[Page 51552]]

 
(2) If any improper installation  Before further      Follow Part I,
 or wrong torque is found during   flight after the    Accomplishment
 any inspection required by        inspection in       Instructions of
 paragraph (e)(1) of this AD,      which any           Raytheon Aircraft
 correct the installation or       improper            Company Mandatory
 torque.                           installation or     Service Bulletin
                                   wrong torque is     No. SB 73-3634,
                                   found.              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 pedestal      inspection          Raytheon Aircraft
 and replacement of the engine     interval or 12      Company Mandatory
 controls cross shaft hardware     calendar months     Service Bulletin
 is the terminating action for     after October 4,    No. SB 73-3634,
 the repetitive inspection and     2004 (the           dated September
 re-torque requirements            effective date of   2003. The
 specified in paragraph (e)(1)     this AD),           applicable
 of this AD.                       whichever occurs    airplane
                                   later. You may do   maintenance
                                   this modification   manual also
                                   before this time    addresses this
                                   as terminating      issue.
                                   action for the
                                   repetitive
                                   inspection and re-
                                   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.

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following the 
instructions in Raytheon Aircraft Company Mandatory Service Bulletin 
No. SB 73-3634, dated September, 2003. The Director of the Federal 
Register approved the incorporation by reference of this service 
bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You 
may get a copy from Raytheon Aircraft Company, 9709 E. Central, 
Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-
3140. You may review copies at FAA, Central Region, Office of the 
Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 
or at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, call (202) 
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Kansas City, Missouri, on August 12, 2004.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-18923 Filed 8-19-04; 8:45 am]
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