[Federal Register Volume 67, Number 137 (Wednesday, July 17, 2002)]
[Proposed Rules]
[Pages 46928-46932]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-17885]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-CE-21-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company 200, 300, and
1900 Series, and Models F90 and A100-1 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain Raytheon Aircraft Company (Raytheon)
200, 300, and 1900 series, and Models F90 and A100-1 airplanes. This
proposed AD would require you to check the airplane logbook to
determine if the elevator(s) have been removed from the airplane. If
the elevator(s) have been removed, this proposed AD would also require
you to inspect the elevator balance weight attachment screws for
correct length, and, if necessary, install new screws that are of
improved design and rebalance the elevator, depending on the results of
the inspection. This proposed AD is the result of the elevator balance
weight attachment screws and balance weights being improperly installed
when balancing the elevator after it had been removed for repair or
repainting. The actions specified by this
[[Page 46929]]
proposed AD are intended to prevent the balance weight attachment
screws from becoming loose. Loose screws could come into contact and
interfere with the horizontal stabilizer. This interference could
restrict elevator movement and result in loss of elevator pitch
control.
DATES: The Federal Aviation Administration (FAA) must receive any
comments on this proposed rule on or before September 16, 2002.
ADDRESSES: Submit comments to FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2001-CE-21-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. You may view any
comments at this location between 8 a.m. and 4 p.m., Monday through
Friday, except Federal holidays. You may also send comments
electronically to the following address: [email protected].
Comments sent electronically must contain ``Docket No. 2001-CE-21-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 text.
You may get service information that applies to this proposed AD
from Raytheon Aircraft Company, P.O. 9709 E. Central, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140. You may also view
this information at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Paul DeVore, Aerospace Engineer, FAA,
Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent
Airport, Wichita, Kansas 67209; telephone: (316) 946-4142; facsimile:
(316) 946-4407.
SUPPLEMENTARY INFORMATION:
Comments Invited
How Do I Comment on This Proposed AD?
The FAA invites comments on this proposed rule. You may submit
whatever written data, views, or arguments you choose. You need to
include the rule's docket number and submit your comments to the
address specified under the caption ADDRESSES. We will consider all
comments received on or before the closing date. We may amend this
proposed rule in light of comments received. Factual information that
supports your ideas and suggestions is extremely helpful in evaluating
the effectiveness of this proposed AD action and determining whether we
need to take additional rulemaking action.
Are There Any Specific Portions of This Proposed AD I Should Pay
Attention to?
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed rule that
might suggest a need to modify the rule. You may view all comments we
receive before and after the closing date of the rule in the Rules
Docket. We will file a report in the Rules Docket that summarizes each
contact we have with the public that concerns the substantive parts of
this proposed AD.
How Can I Be Sure FAA Receives My Comment?
If you want FAA to acknowledge the receipt of your mailed comments,
you must include a self-addressed, stamped postcard. On the postcard,
write ``Comments to Docket No. 2001-CE-21-AD.'' We will date stamp and
mail the postcard back to you.
Discussion
What Events Have Caused This Proposed AD?
Raytheon notified FAA of three incidents in which the elevator
jammed during takeoff and landing on Models 200, B300, and 1900C
airplanes. Investigations showed the cause for the elevator to jam was
that the attachment screws and balance weights were not properly
installed when the elevators were balanced after they were removed for
repair or repainting.
Improperly installed balance weight attachment screws could result
in the screws becoming loose and contacting and interfering with the
horizontal stabilizer. Interference with the horizontal stabilizer
could result in restricted elevator movement.
What Are the Consequences if the Condition Is Not Corrected?
If this condition is not detected and corrected, loose screws could
interfere with the horizontal stabilizer, which could cause restricted
elevator movement. This condition could result in loss of elevator
pitch control.
Is There Service Information That Applies to This Subject?
Raytheon has issued Mandatory Service Bulletin SB 27-3187, Rev. 1,
September, 2001.
What Are the Provisions of This Service Information?
The service bulletin includes procedures for:
--Determining whether the elevator has been removed for repair or
repaint;
--Inspecting the elevator balance weight attachment screws to determine
if they are the correct length;
--Correcting the installation of improperly installed screws; and
--Rebalancing the elevators with new attachment bolts.
The FAA's Determination and an Explanation of the Provisions of This
Proposed AD
What Has FAA Decided?
After examining the circumstances and reviewing all available
information related to the incidents described above, we have
determined that:
--The unsafe condition referenced in this document exists or could
develop on other 200, 300, and 1900 series, and Models F90 and A100-1
airplanes of the same type design;
--Certain actions specified in the previously-referenced service
information should be accomplished on the affected airplanes; and
--AD action should be taken in order to correct this unsafe condition.
What Would This Proposed AD Require?
This proposed AD would require you to check the airplane logbook to
determine if the elevator(s) has/have been removed from the airplane.
If the elevator(s) has/have been removed, this proposed AD would also
require you to inspect the elevator balance weight attachment screws
for correct length, and, if necessary, install new screws that are of
improved design and rebalance the elevator, depending on the results of
the inspection.
Cost Impact
How Many Airplanes Would This Proposed AD Impact?
We estimate that this proposed AD affects 2334 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 the proposed check of
the airplane logbook:
[[Page 46930]]
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Total cost
Labor cost Parts cost Total cost on U.S.
per airplane operators
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1 workhour x $60 = $60.......................... None required..................... $60 $140,040
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We estimate the following costs to accomplish the proposed
inspection of the elevator balance weight attachment screws that would
be required based on the results of the proposed logbook check. We have
no way of determining the number of airplanes that may need such
inspection:
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Total cost
Labor cost Parts cost per airplane
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2 workhours x $60 = $120........... None required........ $120
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We estimate the following costs to accomplish the proposed
replacement of the elevator balance weight attachment screws that would
be required based on the results of the proposed inspection for
airplanes in which the logbook check reveals that further inspection is
necessary. We have no way of determining the number of airplanes that
may need such replacements:
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Total cost
Labor cost Parts cost per airplane
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1 workhour x $60 = $60............. $16 per bolt x 2 $92
bolts per elevator =
$32
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Regulatory Impact
Would This Proposed AD Impact Various Entities?
The regulations proposed herein 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. Therefore, it
is determined that this proposed rule would not have federalism
implications under Executive Order 13132.
Would This Proposed AD Involve a Significant Rule or Regulatory Action?
For the reasons discussed above, I certify that this proposed
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) if
promulgated, 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 draft regulatory
evaluation prepared for this action has been placed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 airworthiness directive
(AD) to read as follows:
Raytheon Aircraft Company: Docket No. 2001-CE-21-AD
(a) What airplanes are affected by this AD? This AD affects the
following airplane models and serial numbers that are certificated
in any category:
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Model Serial Nos.
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(1) F90................................ LA-2 through LA-236.
(2) A100-1 (U-21J)..................... BB-3 through BB-5.
(3) A200 (C-12C)....................... BC-1 through BC-75 and BD-1
through BD-30.
(4) A200C (UC-12B)..................... BJ-1 through BJ-66.
(5) A200CT (C-12D), (C-12F), (RC-12D), BP-1, BP-7 through BP-11, BP-
(FWC-12D), (RC-12G), (RC-12H), (RC- 22, BP-24 through BP-63, FC-1
12K), or (RC-12P). through FC-3, GR-1 through GR-
19, FE-1 through FE-9, FE-25
through FE-36.
(6) B200............................... BB-734, BB-793, BB-829, BB-854
through BB-870, BB-874 through
BB-891, BB-894, BB-896 through
BB-911, and BB-913 through BB-
1652.
(7) B200C.............................. BL-37 through BL-57, BL-61
through BL-72, BL-124 through
BL-140.
(8) B200C (C-12F), (C-12R), (UC-12M), BL-73 through BL-112, BL-118
or (UC-12F). through BL-123, BP-64 through
BP-71, BU-1 through BU-12, BV-
1 through BV-12, and BW-1
through BW-29.
(9) B200CT............................. BN-2 through BN-4, FG-1 and FG-
2.
(10) B200T and 200T.................... BT-1 through BT-38.
(11) 200............................... BB-2, BB-6 through BB-733, BB-
735 through BB-792, BB-794
through BB-828, BB-830 through
BB-853, BB-872, BB-873, BB-
892, BB-893, and BB-912.
(12) 200C.............................. BL-1 through BL-23 and BL-25
through BL-36.
[[Page 46931]]
(13) 200CT............................. BN-1.
(14) 300 and 300LW..................... FA-1 through FA-230 and FF-1
through FF-19.
(15) B300.............................. FL-1 through FL-241.
(16) B300C............................. FM-1 through FM-9 and FN-1.
(17) 1900.............................. UA-2 and UA-3.
(18) 1900C............................. UB-1 through UB-74 and UC-1
through UC-174.
(19) 1900C (C-12J)..................... UD-1 through UD-6.
(20) 1900D............................. UE-1 through UE-358.
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(b) Who must comply with this AD? Anyone who wishes to operate
any of the airplanes identified in paragraph (a) of this AD must
comply with this AD.
(c) What problem does this AD address? The actions specified by
this AD are intended to prevent the balance weight attachment screws
from becoming loose. Loose screws could come into contact and
interfere with the horizontal stabilizer. This interference could
restrict elevator movement and result in loss of elevator pitch
control.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) Check the airplane logbook to determine Within the next 200 No special procedures required to check
whether the elevator(s) has/have been hours time-in-service the logbook. Raytheon Mandatory Service
removed. The owner/operator holding at (TIS) after the Bulletin SB 27-3187, Rev. 1, Revised:
least a private pilot certificate as effective date of this September, 2001, references this airplane
authorized by section 43.7 of the Federal AD. logbook check.
Aviation Regulations (14 CFR 43.7) may
check the airplane logbook.
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(2) If, by checking the airplane logbook: Within the next 200 In accordance with the Accomplishment
(i) the pilot can positively show that hours time-in-service Instructions section of Raytheon
both elevators have never been removed, (TIS) after the Mandatory Service Bulletin SB 27-3187,
then the requirements of paragraphs effective date of this Rev. 1, Revised: September, 2001.
(d)(2)(ii) and (d)(3) of this AD do not AD.
apply. You must make an entry into the
aircraft records that shows compliance
with this portion of the AD, in accordance
with section 43.9 of the Federal Aviation
Regulations (14 CFR 43.9).
(ii) the pilot identifies that the
elevator(s) has/have been removed, or if
complete records of elevator(s) do not
exist, inspect the elevator balance weight
attachment screws to determine if they are
the correct length
(3) If, during the inspection required in Not Applicable......... In accordance with the Accomplishment
paragraph (d)(2)(ii) of this AD, the Instructions section of Raytheon
elevator balance weight attachment screws Mandatory Service Bulletin SB 27-3187,
are found to be the correct length, Rev. 1, Revised: September, 2001.
paragraph (d)(4) of this AD does not apply.
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(4) If, during the inspection required in Prior to further flight In accordance with the Accomplishment
paragraph (d)(2)(ii) of this AD, the after the inspection Instructions section of Raytheon
elevator balance weight attachment required in paragraph Mandatory Service Bulletin SB 27-3187,
screw(s) is/are found to be the incorrect (d)(2)(ii) of this AD. Rev. 1, Revised: September, 2001, and the
the length, remove and rebalance applicable maintenance manual.
elevator(s) by installing the balance
weights with the appropriate new elevator
balance weight attachment bolts, part
number (P/N) in the range of NAS6703HU12
through NAS6703HU22, that have drilled
heads and are secured with safety wire,
and re-install the elevator.
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(5) Do not install, on any affected As of the effective Not applicable.
airplane, an elevator that has been date of this AD.
rebalanced unless it has been rebalanced
by installing the balance weights with the
appropriate new elevator balance weight
attachment bolts, P/N in the range of
NAS6703HU12 through NAS6703HU22, that have
drilled heads and are secured with safety
wire.
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Note 1: The compliance times specified in Raytheon Mandatory
Service Bulletin SB 27-3187, Rev. 1, Revised: September, 2001, are
different from those required by this AD. The compliance times in
this AD take precedence over those in the service bulletin.
(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 2: 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
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.
[[Page 46932]]
(f) Where can I get information about any already-approved
alternative methods of compliance? Contact Paul DeVore, Aerospace
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316)
946-4142; 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) How do I get copies of the documents referenced in this AD?
You may get copies of the documents referenced in this AD from
Raytheon Aircraft Company, P.O. Box 85, 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 July 9, 2002.
Michael K. Dahl,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-17885 Filed 7-16-02; 8:45 am]
BILLING CODE 4910-13-P