[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).

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

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]]



----------------------------------------------------------------------------------------------------------------
                                                                                                     Total cost
                   Labor cost                                 Parts cost               Total cost      on U.S.
                                                                                      per airplane    operators
----------------------------------------------------------------------------------------------------------------
1 workhour x $60 = $60..........................  None required.....................           $60      $140,040
----------------------------------------------------------------------------------------------------------------

    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:

------------------------------------------------------------------------
                                                             Total cost
             Labor cost                    Parts cost       per airplane
------------------------------------------------------------------------
2 workhours x $60 = $120...........  None required........          $120
------------------------------------------------------------------------

    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:

------------------------------------------------------------------------
                                                             Total cost
             Labor cost                    Parts cost       per airplane
------------------------------------------------------------------------
1 workhour x $60 = $60.............  $16 per bolt x 2                $92
                                      bolts per elevator =
                                      $32
------------------------------------------------------------------------

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:

------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
(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.
------------------------------------------------------------------------

    (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:

----------------------------------------------------------------------------------------------------------------
                  Actions                           Compliance                        Procedures
----------------------------------------------------------------------------------------------------------------
(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.
ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½--------------------------------------------------------------------
(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.
ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½--------------------------------------------------------------------
(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.
ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½ï¿½--------------------------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------


    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