FR Doc 04-9105

[Federal Register: April 22, 2004 (Volume 69, Number 78)]
[Proposed Rules]
[Page 21768-21771]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22ap04-23]

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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).

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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: 9-ACE-7-Docket@faa.gov. 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:

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Total cost per Total cost on U.S.
Labor cost Parts cost airplane operators
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1 workhour X $65 per hour = $65......... Not Applicable............ $65 $65 X 5,025 = $326,625
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We estimate the following costs to do the proposed modification of
the pedestal and replacement of the engine controls cross shaft
hardware:

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

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Model Serial Numbers
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(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.
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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:

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Actions Compliance Procedures
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(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.
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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]

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