[Federal Register Volume 61, Number 203 (Friday, October 18, 1996)]
[Proposed Rules]
[Pages 54372-54373]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-26699]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-CE-44-AD]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Corporation (Formerly
Beech Aircraft Corporation) 35 Series 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 Corporation
(Raytheon) 35 series airplanes. The proposed action would require
inspecting the ruddervator differential tail control rod assembly for
corrosion or cracks, repairing or replacing any cracked or corroded
part, and applying anti-corrosion sealant to the ruddervator control
pushrods. The proposed action results from a split in the ruddervator
control push rod on an affected airplane that was found during a
routine inspection. The split occurred when water froze in the internal
area of the control push rod and then expanded. The actions specified
by the proposed AD are intended to prevent failure of the differential
tail control rod assembly, which could result in loss of control of the
airplane.
DATES: Comments must be received on or before December 20, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 96-CE-44-AD, Room 1558, 601 E.
12th Street, 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 Corporation, P.O. Box 85, Wichita, Kansas
67201-0085. This information also may be examined at the Rules Docket
at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Larry Engler, Aerospace Safety
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport
Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316)
946-4122; facsimile (316) 946-4407.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA-public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 96-CE-44-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 96-CE-44-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has received a report of the ruddervator control pushrod
splitting on a Raytheon 35 series airplane; specifically a \3/4\-inch
longitudinal split was found in the left ruddervator control pushrod.
The splitting is attributed to water freezing in the internal area of
the control push rod.
The design of the ruddervator differential tail control rod
assembly is that the two rods have a hollow shaft that is open at both
ends and extends through the length of the rod. Moisture laden air is
entering the rod assembly through these hollow shafts and then
condenses in the rod assembly tube. When the moisture accumulates, it
freezes in cold weather, expands, and causes the ruddervator control
pushrod to split. This condition could lead to failure of the
ruddervator differential tail control rod asssembly and subsequent loss
of control of the airplane.
Applicable Service Information
Raytheon has issued Service Bulletin (SB) No. 2668, dated September
1996, which specifies procedures for inspecting the ruddervator
differential tail control rod assembly, and repairing or replacing any
cracked part. Raytheon SB No. 2668 also specifies procedures for
applying an anti-corrosion sealant to the ruddervator control pushrods.
This service bulletin applies to certain serial numbers (D-1 through
D10403, D-15001, and D-15002) of the following models of Raytheon 35
series airplanes:
35 35R A35 B35
C35 D35 E35 F35
G35 H35 J35 K35
M35 N35 P35 S35
V35 V35-TC V35A V35A-TC
V35B V35B-TC ................ ............
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, including the
referenced service information, the FAA has determined that AD action
should be taken to prevent failure of the ruddervator differential tail
control rod assembly, which could result in loss of control of the
airplane.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Raytheon 35 series
[[Page 54373]]
airplanes of the same type design, the proposed AD would require
inspecting the ruddervator differential tail control rod assembly for
corrosion or cracks, repairing or replacing any cracked or corroded
part, and applying corrosion sealant to the ruddervator control
pushrods. Accomplishment of the proposed actions would be in accordance
with Raytheon SB No. 2668, dated September 1996.
Cost Impact
The FAA estimates that 10,405 airplanes in the U.S. registry would
be affected by the proposed AD, that it would take approximately 4
workhours per airplane to accomplish the proposed inspection and anti-
corrosion sealant application, and that the average labor rate is
approximately $60 an hour. Based on these figures, the total cost
impact of the proposed AD on U.S. operators is estimated to be
$2,497,200. This figure is based on the assumption that none of the
affected airplanes would have a corroded or cracked part in the
ruddervator differential tail control rod assembly that would need to
be repaired or replaced. The FAA has no way of determining how many
ruddervator control push rods that would be corroded or cracked.
Regulatory Impact
The regulations proposed herein would not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
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, pursuant to 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. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
Raytheon Aircraft Corporation (formerly Beech Aircraft Corporation):
Docket No. 96-CE-44-AD.
Applicability: Models 35, 35R, A35, B35, C35, D35, E35, F35,
G35, H35, J35, K35, M35, N35, P35, S35, V35, V35TC, V35A, V35A-TC,
V35B, and V35B-TC airplanes (serial numbers D-1 through D-10403, D-
15001, and D-15002), certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, 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 (d) 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 the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it. Compliance: Required within the next 100 hours time-in-
service after the effective date of this AD, unless already
accomplished.
To prevent failure of the ruddervator differential tail control
rod assembly, which could result in loss of control of the airplane,
accomplish the following:
(a) Inspect the ruddervator differential tail control rod
assembly for cracks and corrosion in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Raytheon Service Bulletin
(SB) No. 2668, dated September 1996. Prior to further flight, repair
or replace any corroded or cracked part as specified in and in
accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon
SB No. 2668, dated September 1996.
(b) Apply anti-corrosion sealant to the ruddervator control
pushrods in accordance with the ACCOMPLISHMENT INSTRUCTIONS section
of Raytheon SB No. 2668, dated September 1996.
(c) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Wichita Aircraft Certification Office
(ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita,
Kansas 67209. The request shall be forwarded through an appropriate
FAA Maintenance Inspector, who may add comments and then send it to
the Manager, Wichita ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(e) All persons affected by this directive may obtain copies of
the document referred to herein upon request to the Raytheon
Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; or
may examine this document at the FAA, Central Region, Office of the
Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
Issued in Kansas City, Missouri, on October 10, 1996.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-26699 Filed 10-17-96; 8:45 am]
BILLING CODE 4910-13-U
