(a) What airplanes are affected by this AD? This AD affects the
following airplanes that are certificated in any category:
(1) Beech Models C35, D35, E35, F35, G35, H35, J35, K35, M35,
N35, and P35 airplanes, all serial numbers; and
(2) Beech Models S35, V35, V35A, and V35B airplanes, all serial
numbers, that do not have the straight tail conversion modification
incorporated in accordance with Supplemental Type Certificate (STC)
SA2149CE.
NOTE 1: Beech Models 35, 35R, A35, B35 airplanes were included
in the Applicability of AD 94-20-04. We have removed Beech Models
35, 35R, A35, and B35 airplanes from the Applicability section of
this AD and incorporated the actions applicable to these airplanes
into another AD action. Part of this other AD action is the
incorporation of Raytheon Service Raytheon Service Bulletin 27-3358.
(b) Who must comply with this AD? Anyone who wishes to operate
any of the airplanes identified in paragraphs (a), (a)(1), and
(a)(2) 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 structural failure of the V-tail,
which could result in loss of control of the airplane.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Verify that the Accomplish the Verify in accordance
ruddervator balance is verification within with the applicable
within manufacturer's the next 100 hours the shop or
specified limits as defined TIS after November maintenance manual.
in the applicable shop or 28, 1994 (the Balance the
maintenance manual. If the effective date of ruddervator control
ruddervator is outside the AD 94-20-04) and surfaces in
specified limits, balance thereafter prior to accordance with
the ruddervator control further flight Section 3 of Beech
surfaces. after the Shop Manual 35-
ruddervators are 590096B19, or
repaired or subsequent
repainted (even if revisions.
stripes are added
or paint is touched
up).
Accomplish the
balancing prior to
further flight
after the
ruddervator is
found outside the
specified limits.
-----------------------------
(2) Visually inspect the Inspect and set the In accordance with
empennage, aft fuselage, controls, tension, the procedures and
and ruddervator control and rigging within as specified in the
system for damage. the next 100 hours instructions to
(i) Repair or replace any TIS after November Beech Kit 35-4017-1
damaged parts; and. 28, 1994 (the ``Kit Information
(ii) Set the elevator effective date of Empennage and Aft
controls, rudder and tab AD 94-20-04). Fuselage
system controls, cable Accomplish any Inspection'', as
tensions, and rigging.. repairs and specified in Beech
replacements prioir Service Bulletin
to further flight No. 2188, dated
after the May, 1987.
inspection.
-----------------------------
(3) Accomplish the following Initially inspect In accordance with
actions: within the 100 the procedures in
(i) Visually inspect the hours time-in- the instructions to
fuselage bulkheads at procedures after Beech Kit 35-4017-1
Fuselage Station (FS) 256.9 the effective date ``Kit Information
and FS 272 for damage of this AD. Empennage & Aft
(cracks, distortion, loose Repetitively Fuselage
rivets, etc.);. inspect thereafter Inspection'', as
(ii) Visually inspect the at intervals not to specified in Beech
fuselage skin around the exceed 100 hours SB 2188, dated May
bulkhead for damage TIS. Repair or 1987.
(wrinkles or cracks); and. replace prior to
(iii) Repair or replace any further flight
damaged parts.. where damage is
found.
-----------------------------
(4) Remove all external Within the next 100 In accordance with
stabilizer reinforcements hours TIS after the applicable
installed during November 28, 1994 maintenance
incorporation of either (the effective date information.
Supplement Type Certificate of AD 94-20-04),
(STC) SA845GL, STC SA846GL, unless already
STC SA1650CE, STC SA2286NM, accomplished.
or STC SA2287NM, as
applicable.
(i) Seal or fill any
residual holes with
appropriate size rivets..
(ii) The internal stub spar
incorporated through STC
SA1649CE and STC SA1650CE
may be retained..
(iii) The external angles
incorporated through STC
SA1649CE may also be
retained by properly
trimming the leading edges
section to permit
installation of the
stabilizer reinforcement
referenced in paragraph
(d)(5)(i) of this AD..
(iv) For the Beech Models
S35, V35, V35A, and V35B
airplanes, you may retain
and use the tail-safe
external angles that were
installed in accordance
with STC SA1649CE instead
of the stabilizer
reinforcement specified in
paragraph (d)(5)(i) of this
AD..
-----------------------------
(5) Accomplish the Within the next 100 In accordance with
following: hours TIS after RAC Kit No. 35-4016-
(i) Install stablizer November 28, 1994 3, 35-4016-5, 35-
reinforcements;. (the effective date 4016-7, or 35-4016-
(ii) Set the elevator of AD 94-20-04), 9, as applicable
nosedown trim; and. unless already and as specified in
(iii) Replace the accomplished. Beech SB No. 2188,
ruddervator tab control dated May, 1987.
cables with larger diameter
cables..
-----------------------------
(6) Verify the accuracy of Accomplish the Use the procedures
the airplane basic weight airplane basic contained in the
and balance information and weight and balance Appendix to this
correct any discrepancies. accuracy AD.
verification within
the next 100 hours
TIS after November
28, 1994 (the
effective date the
of AD 94-20-04),
unless already
accomplished.
Correct any
discrepancies.
prior to further
flight after the
verification.
------------------------------------------------------------------------
(e) Can I comply with this AD in any other way?
(1) You may use an alternative method of compliance or adjust
the compliance time if:
(i) Your alternative method of compliance provides an equivalent
level of safety; and
(ii) 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.
(2) Alternative methods of compliance approved in accordance
with AD 94-20-04 R1 or AD 94-20-04 are approved as alternative
methods of compliance with this AD.
NOTE 2: This AD applies to each airplane identified in
paragraphs (a), (a)(1), and (a)(2) 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 Mr. T.N. Baktha, Aerospace
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316)
946-4155; 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 obtain copies of the documents referenced in this AD from the
Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201-0085. You
may examine these documents at FAA, Central Region, Office of the
Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.
(i) Does this AD action affect any existing AD actions? This
amendment revises AD 94-20-04 R1, Amendment 39-12919.
__________ Appendix to Docket No. 93-CE-37-AD _______________
Weight and Balance Accuracy Method No. 1
1. Review existing weight and balance documentation to assure
completeness and accuracy of the documentation from the most recent
FAA-approved weighing or from factory delivery to date of compliance
with this AD.
2. Compare the actual configuration of the airplane to the
configuration described in the weight and balance documentation.
3. If equipment additions or deletions are not reflected in the
documentation or if modifications affecting the location of the
center of gravity (e.g., paint or structural repairs) are not
documented, determine the accuracy of the airplane weight and
balance data in accordance with Method No. 2.
Weight and Balance Information Accuracy Method No. 2
1. Determine the basic empty weight and center of gravity (CG)
of the empty airplane using the Weighing Instructions in the Weight
and Balance section of the airplane flight manual/pilot's operating
handbook (AFM/POH).
2. Record the results in the airplane records, and use these new
values as the basis for computing the weight and CG information as
specified in the Weight and Balances section of the AFM/POH.
Issued in Kansas City, Missouri, on January 15, 2003.
Michael Gallagher, Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 03-1678 Filed 1-24-03; 8:45 am]
DATES: The Federal Aviation Administration (FAA) must receive any
comments on this proposed rule on or before March 3, 2003.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-CE-37-AD]
RIN 2120-AA64
AIRWORTHINESS DIRECTIVES; Raytheon Aircraft Company Beech Models
C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A,
and V35B Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes to revise Airworthiness Directive (AD)
94-20-04 R1, which currently requires ruddervator inspections and
modifications on certain Raytheon Aircraft Company (Raytheon) Beech
Models C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35,
V35A, and V35B airplanes. This proposed AD is the result of the need to
add a repetitive inspection of the fuselage bulkheads and change other
inspections from a repetitive to a one-time action. The proposed AD
would make these changes to AD 94-20-04 R1. The actions specified by
the proposed AD are intended to prevent structural failure of the V-
tail, which could result in loss of control of the airplane.
DATES: The Federal Aviation Administration (FAA) must receive any
comments on this proposed rule on or before March 3, 2003.
ADDRESSES: Submit comments in triplicate to FAA, Central Region, Office
of the Regional Counsel, Attention: Rules Docket No. 93-CE-37-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. Comments may be
inspected at this location between 8 a.m. and 4 p.m., Monday through
Friday, holidays excepted.
Service information that applies to the proposed AD may be obtained
from the Raytheon Aircraft Company, PO Box 85, Wichita, Kansas 67201-
0085; telephone: (800) 625-7043 or (316) 676-4556. This information
also may be examined at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. T.N. Baktha, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4155;
facsimile: (316) 946-4407.
SUPPLEMENTARY INFORMATION:
Comments Invited
How Do I Comment on the 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 in triplicate
to the address specified under the caption ADDRESSES. The FAA will
consider all comments received on or before the closing date. We may
amend the proposed rule in light of comments received. Factual
information that supports your ideas and suggestions is extremely
helpful in evaluating the effectiveness of the proposed AD action and
determining whether we need to take additional rulemaking action.
Are There Any Specific Portions of the Proposed AD I Should Pay
Attention to?
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule that
might suggest a need to modify the rule. You may examine 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
FAA contact with the public that concerns the substantive parts of the
proposed AD.
How Can I Be Sure FAA Receives My Comment?
If you want us to acknowledge the receipt of your comments, you
must include a self-addressed, stamped postcard. On the postcard, write
"Comments to Docket No. 93-CE-37-AD." We will date stamp and mail the
postcard back to you.
Discussion
Has FAA Taken Any Action to This Point?
On October 15, 2002, FAA issued AD 94-20-04 R1, Amendment 39-12919
(67 FR 64794, October 22, 2002), to require ruddervator inspections and
modifications on certain Raytheon Aircraft Company (Raytheon) Beech
Models C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35,
V35A, and V35B airplanes.
The intent of this AD was to maintain the inspection and
modification requirements of AD 94-20-04, Amendment 39-9032 (59 FR
49785, September 30, 1994), but condense and clarify the information
presented in AD 94-20-04.
What Has Happened Since AD 94-20-04 R1 To Initiate This Action?
Comments from the public since issuance of AD 94-20-04 R1 indicate
a need for a revision to that AD. Specifically, the visual inspection
of the empennage, aft fuselage, and ruddervator control system with any
subsequent repair and the setting of the elevator controls, rudder and
tab system controls, cable tensions, and rigging should all be a one
time action. Currently, they are to be accomplished repetitively at
100-hour time-in-service (TIS) intervals.
In addition, we inadvertently did not include the 100-hour TIS
interval repetitive inspections of the fuselage bulkheads that were
required by AD 94-20-04.
The FAA's Determination and Explanation of the Provisions of the
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 still exists or could
develop on other Raytheon Beech Models C35, D35, E35, F35, G35, H35,
J35, K35, M35, N35, P35, S35, V35, V35A, and V35B of the same type
design;
--The actions of AD 94-20-04 R1 should be maintained except for adding the
fuselage bulkhead inspections and making certain repetitive actions a
one -time action; and
--AD action should be taken in order to continue to prevent structural
failure of the V-tail, which could result in loss of control of
the airplane.
What Would the Proposed AD Require?
This proposed AD would revise AD 94-20-04 R1, which applies to
Raytheon Beech Models C35, D35, E35, F35, G35, H35, J35, K35, M35, N35,
P35, S35, V35, V35A, and V35B. The proposed AD would:
--Maintain the actions of AD 94-20-04 R1, but would make the repetitive
visual inspection of the empennage, aft fuselage, and ruddervator
control system with any subsequent repair and the setting of the
elevator controls, rudder and tab system controls, cable tensions, and
rigging a one time action; and
--Would add repetitive inspections of the fuselage bulkheads that were
required by AD 94-20-04.
Cost Impact
How Many Airplanes Would the Proposed AD Impact?
We estimate that the proposed AD affects 10,200 airplanes in the
U.S. registry.
What Would Be the Cost Impact of the Proposed AD on Owners/Operators of
the Affected Airplanes?
We estimate the following costs to accomplish the proposed initial
inspections. These cost figures are exactly the same as what is
currently required by AD 94-20-04 R1. Although we are adding the
inspection of the fuselage bulkheads to the proposed AD, we had already
incorporated the costs of this inspection into the Cost Impact of AD
94-20-04 R1. Therefore, this proposed AD presents no new costs upon the
public:
-----------------------------------------------------------------------------------
Total cost per Total cost on
Labor cost Parts cost airplane U.S. operators
-----------------------------------------------------------------------------------
40 workhours at $60 ........ Not applicable.... $2,400 $24,480,000
per hour = $2,400
-----------------------------------------------------------------------------------
The above figures are based only on the initial inspections and do
not take into account the cost of repetitive inspections or
adjustments, repairs, or replacements that would be necessary based on
the results of the inspections. We have no way of determining the
number of repetitive inspections each owner/operator of the affected
airplanes would incur or what adjustments, repairs, or replacements may
be necessary based on the results of the inspections.
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 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 14
CFR part 39 of the Federal Aviation Regulations 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 removing Airworthiness Directive (AD)
94-20-04
R1, Amendment 39-12919 (67 FR 64794, October 22, 2002), and by adding a
new AD to read as follows: