[Federal Register: November 20, 2002 (Volume 67, Number 224)]
[Rules and Regulations]
[Page 69996-69999]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20no02-4]
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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
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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
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2 workhours x $60 = $120....... None required......... $120
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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:
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Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
1 workhour x $60 = $60......... $16 per bolt x 2 bolts $92
per elevator = $32.
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[[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.
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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
(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 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.
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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.
(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]
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