[Federal Register Volume 67, Number 224 (Wednesday, November 20, 2002)]
[Rules and Regulations]
[Pages 69996-69999]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-29132]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-21-AD; Amendment 39-12955; AD 2002-23-11]
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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Raytheon Aircraft Company (Raytheon) 200, 300, and 
1900 series, and Models F90 and A100-1 airplanes. This AD requires 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 AD also requires you to inspect the elevator balance 
weight attachment screws for correct length, and, if necessary, install 
new bolts that are of improved design and rebalance the elevator, 
depending on the results of the inspection. This 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 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: This AD becomes effective on January 10, 2003.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulations as of 
January 10, 2003.

ADDRESSES: You may get the service information referenced in this AD 
from Raytheon Aircraft Company, P.O. 9709 E. Central, Kansas 67201-
0085; telephone: (800) 429-5372 or (316) 676-3140. You may view this 
information at the Federal Aviation Administration (FAA), Central 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2001-CE-21-AD, 901 Locust, Room 506, Kansas City, Missouri 64106; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

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:

Discussion

What Events Have Caused This 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

[[Page 69997]]

screws becoming loose and contacting and interfering with the 
horizontal stabilizer. Interference with the horizontal stabilizer 
could result in restricted elevator movement.

What Is the Potential Impact if FAA Took no Action?

    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.

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 200, 300, and 1900 series, and Models F90 and A100-1 
airplanes. This proposal was published in the Federal Register as a 
notice of proposed rulemaking (NPRM) on July 17, 2002 (67 FR 46928). 
The NPRM proposed to 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, the NPRM would also require 
you to inspect the elevator balance weight attachment screws for 
correct length, and, if necessary, install new bolts that are of 
improved design and rebalance the elevator, depending on the results of 
the inspection.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in the making 
of this amendment. The following presents the comment received on the 
proposal and FAA's response to comment:

Comment Issue: Replace All Elevator Balance Weight Attachment Screws

What Is the Commenter's Concern?

    The commenter states that if the purpose of the proposed AD is to 
prevent the elevator balance weight attachment screws from becoming 
loose, then all elevator balance weight attachment screws should be 
replaced with the new bolts, or at the very least, when the elevators 
are removed for any reason.

What Is FAA's Response to the Concern?

    We do not concur with the commenter. According to reports and 
service history, only elevators that were removed and rebalanced (such 
as would occur after repainting) were reinstalled with incorrect length 
screws. We have not received any reports of elevator balance weight 
attachment screws becoming loose on airplanes in which an elevator had 
not been removed and rebalanced.
    Unless an elevator has been removed and rebalancing is necessary, 
we have no justification for replacing the elevator balance weight 
attachment screws with the new bolts when an elevator is removed and 
reinstalled and rebalancing is not necessary.
    In paragraph (d)(5) of the proposed AD, we address installing the 
new balance weight attachment bolts any time an elevator is removed and 
rebalancing is necessary.
    We have not changed the final rule AD based on this comment.

FAA's Determination

What Is FAA's Final Determination on This Issue?

    After careful review of all available information related to the 
subject presented above, we have determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. We have determined that these minor 
corrections:

--Provide 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.

Cost Impact

How Many Airplanes Does This AD Impact?

    We estimate that this AD affects 2,334 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 accomplish the check of the 
airplane logbook:

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

    We estimate the following costs to accomplish the inspection of the 
elevator balance weight attachment screws that will be required based 
on the results of the logbook check. We have no way of determining the 
number of airplanes that will need such inspection:

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

    We estimate the following costs to accomplish the replacement of 
the elevator balance weight attachment screws that will be required 
based on the results of the 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 will need such 
replacements:

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


[[Page 69998]]

Regulatory Impact

Does This AD Impact Various Entities?

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    For the reasons discussed above, I certify that this 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) 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 final evaluation prepared for this 
action is contained 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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

    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 AD to read as follows:

2002-23-11 Raytheon Aircraft Company: Amendment 39-12955; 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
(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    Within the next     No special
 to determine whether the          200 hours time-in-  procedures
 elevator(s) has/have been         service (TIS)       required to check
 removed. The owner/operator       after January 10,   the logbook.
 holding at least a private        2003 (the           Raytheon
 pilot certificate as authorized   effective date of   Mandatory Service
 by section 43.7 of the Federal    this AD).           Bulletin SB 27-
 Aviation Regulations (14 CFR                          3187, Rev. 1,
 43.7) may check the airplane                          Revised:
 logbook.                                              September, 2001,
                                                       references this
                                                       airplane logbook
                                                       check.

[[Page 69999]]

 
(2) If, by checking the airplane  Within the next     In accordance with
 logbook:.                         200 hours time-in-  the
(i) the pilot can positively       service (TIS)       Accomplishment
 show that both elevators have     after January 10,   Instructions
 never been removed, then the      2003, (the          section of
 requirements of paragraphs        effective date of   Raytheon
 (d)(2)(ii) and (d)(3) of this     this AD).           Mandatory Service
 AD do not apply. You must make                        Bulletin SB 27-
 an entry into the aircraft                            3187, Rev. 1,
 records that shows compliance                         Revised:
 with this portion of the AD, in                       September, 2001.
 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     Not applicable....  In accordance with
 required in paragraph                                 the
 (d)(2)(ii) of this AD, the                            Accomplishment
 elevator balance weight                               Instructions
 attachment screws are found to                        section of
 be the correct length,                                Raytheon
 paragraph (d)(4) of this AD                           Mandatory Service
 does not apply.                                       Bulletin SB 27-
                                                       3187, Rev. 1
                                                       Revised:
                                                       September, 2001.
(4) If, during the inspection     Prior to further    In accordance with
 required in paragraph             flight after the    the
 (d)(2)(ii) of this AD, the        inspection          Accomplishment
 elevator balance weight           required in         Instructions
 attachment screw(s) is/are        paragraph           section of
 found to be the incorrect         (d)(2)(ii) of       Raytheon
 length, remove and rebalance      this AD.            Mandatory Service
 the elevator(s) by installing                         Bulletin SB 27-
 the balance weights with the                          3187, Rev. 1,
 appropriate new elevator                              Revised:
 balance weight attachment                             September, 2001,
 bolts, part number (P/N) in the                       and the
 range of NAS6703HU12 through                          applicable
 NAS6703HU22, that have drilled                        maintenance
 head and are secured with                             manual.
 safety wire, and re-install the
 elevator.
(5) Do not install, on any        As of January 10,   Not applicable.
 affected airplane, an elevator    2003 (the
 that has been rebalanced unless   effective date of
 it has been rebalanced by         this AD).
 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.

    (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 
Sec. Sec.  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) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance with 
Raytheon Mandatory Service Bulletin SB 27-3187, Rev. 1, Revised: 
September, 2001. The Director of the Federal Register approved this 
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You 
may get copies from Raytheon Aircraft Company, P.O. Box 85, Wichita, 
Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. You may 
view copies at the FAA, Central Region, Office of the Regional Counsel, 
901 Locust, Room 506, Kansas City, Missouri, or at the Office of the 
Federal Register, 800 North Capitol Street, NW, suite 700, Washington, 
DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on January 10, 2003.


    Issued in Kansas City, Missouri, on November 12, 2002.
Dorenda D. Baker,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-29132 Filed 11-19-02; 8:45 am]
BILLING CODE 4910-13-P