[Federal Register Volume 61, Number 190 (Monday, September 30, 1996)]
[Proposed Rules]
[Pages 51064-51066]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-24889]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-158-AD]
RIN 2120-AA64
Airworthiness Directives; Beech Model 400A, 400T (Military T-1A),
and 400T (Military TX) Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Beech Model 400A
and 400T series airplanes, that currently requires an inspection of
certain flap roller retention components to detect discrepant or
missing parts; replacement of those parts; and installation of new
washers on the roller attach bolts. This proposed action would require
the replacement of certain previously-installed washers with new and
stronger washers. It would also expand the applicability of the rule to
include additional airplanes. This proposal is prompted by reports
indicating that some locking tab washers on the roller attach bolt
could fail, due to the absence of an inner tang. The actions specified
by the proposed AD are intended to prevent the loss of roller attach
nuts and the flap roller, which could result in the loss of a flap when
the airplane is subject to load limit conditions, and, consequently
lead to reduced controllability of the airplane.
DATES: Comments must be received by November 8, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-158-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Raytheon Aircraft Corporation, Commercial Service
Department, P.O. Box 85, Wichita, Kansas 67201-0085. This information
may be examined at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington, or the FAA, Wichita Aircraft
Certification Office, Small Airplane Directorate, 1801 Airport Road,
Room 100, Mid-Continent Airport, Wichita, Kansas.
FOR FURTHER INFORMATION CONTACT: Larry Engler, Aerospace Engineer,
Airframe Branch, ACE-115W, FAA, Wichita Aircraft Certification Office,
Small Airplane Directorate, 1801 Airport Road, Room 100, Mid-Continent
Airport, Wichita, Kansas 67209; telephone (316) 946-4122; fax (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 shall 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 summarizing 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 Number 96-NM-158-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, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 96-NM-158-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On June 23, 1994, the FAA issued AD 94-14-06, amendment 39-8958 (59
FR 35234, July 11, 1994), applicable to certain Beech Model 400A and
400T (Military T-1A) series airplanes. That AD requires a one-time
inspection of the flap roller retention components to detect discrepant
or missing parts; the replacement of such parts, if necessary; and the
installation of new washers, tab washers, and flat washers on the
roller attach bolts.
That action was prompted by reports indicating that some locking
washers were missing inner tabs; such discrepancies would prevent these
washers from locking. The requirements of that AD are intended to
prevent loss of the main or aft flap surface, which could lead to
reduced controllability of the airplane.
[[Page 51065]]
Actions Since Issuance of Previous Rule
Since the issuance of that AD, the FAA has received reports
indicating that the locking washers that were required to be installed
by AD 94-14-06 are missing tabs, have undersized tabs, or lack inner
tangs; any such discrepancy would prevent a locking washer from
functioning. This condition, if not corrected, could ultimately result
in the loss of a flap and reduced controllability of the airplane. (No
such failures have occurred, however.) Recently, improved locking
washers have been developed that will preclude the new problems that
have been identified.
In addition, the manufacturer has advised the FAA that additional
airplanes--Model 400T (military TX) series airplanes--have been
identified that are subject to the unsafe condition addressed by AD 94-
14-06. These airplanes were not included in the applicability of that
AD.
Explanation of Relevant Service Information
The FAA has reviewed and approved Raytheon Service Bulletin No.
2522, Revision 1, dated May 1996. The original issue of this service
bulletin was referenced in AD 94-14-06 as the appropriate source of
service information. This revised service bulletin describes the
following:
1. Procedures for replacement of the washers, tab washers, and flat
washers on roller attach bolts of the left and right flaps that were
previously installed in accordance with the original issue of the
service bulletin and in accordance with the requirements of AD 94-14-
06. These are to be replaced with new washers, tab washers (which are
also stronger) and flat washers.
2. New procedures for inspecting and replacing, if necessary,
roller attach nuts and bolts; and for installing the new washers, tab
washers (which are also stronger), and flat washers on those bolts.
The revised service bulletin also includes additional airplanes in
its effectivity listing that have been identified as subject to the
same problems that prompted the issuance of the service bulletin (and
AD 94-14-06).
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would supersede AD 94-14-06. It would require the following
actions:
1. For airplanes that have been inspected previously, and on which
the washers, tab washers, and flat washers have been installed in
accordance with AD 94-14-06: Those washers would be required to be
replaced with new washers (including the stronger tab washers).
2. For airplanes that have not been inspected previously and have
not had the washers, tab washers, and flat washers replaced; and for
airplanes that were not included in the applicability of AD 94-14-06:
These airplanes would be required to be inspected for discrepancies in
the roller attach nuts and bolts of the flaps would be required, and
discrepant parts replaced. In addition, the new washers, including the
stronger tab washers, would be required to be installed on the attach
bolts.
These proposed actions would be required to be accomplished in
accordance with the Raytheon service bulletin described previously.
Cost Impact
There are approximately 212 Beech Model 400A and 400T series
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 183 airplanes of U.S. registry would be affected by this
proposed AD.
It is estimated that 102 of the U.S.-registered airplanes would be
required to have the washers replaced with new and stronger washers.
This action would take approximately 2 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts would cost approximately $25 per airplane. Based on these
figures, the cost impact of the proposed replacement action on U.S.
operators of these airplanes is estimated to be $14,790, or $145 per
airplane.
It is estimated that 81 of the U.S.-registered airplanes would be
required to be inspected for discrepancies of the roller attach nuts
and bolts, and would require the installation of new washers. Those
actions would take approximately 6 work hours per airplane to
accomplish, at an average labor rate of $60 per work hour. Required
parts would cost approximately $100 per airplane. Based on these
figures, the cost impact of the proposed actions on U.S. operators of
these airplanes is estimated to be $37,260, or $460 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed requirements
of this AD action, and that no operator would accomplish those actions
in the future if this AD were not adopted.
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 proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the 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 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, 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 removing amendment 39-8958 (59 FR
35234, July 11, 1994), and by adding a new airworthiness directive
(AD), to read as follows:
Beech Aircraft Corporation: Docket 96-NM-158-AD. Supersedes AD 94-
14-06, Amendment 39-8958.
Applicability: Model 400A and 400T series airplanes; as listed
in Beech Service Bulletin No. 2522, dated January 1994, and Raytheon
Service Bulletin No. 2522, Revision 1, dated May 1996; certificated
in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise modified, altered, or repaired in
[[Page 51066]]
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 as indicated, unless accomplished
previously.
To prevent loss of roller attach nuts and the flap roller, which
could result in the loss of a flap when the airplane is subject to
load limit conditions, and consequently lead to reduced
controllability of the airplane; accomplish the following:
(a) For airplanes listed in Beech Service Bulletin No. 2522,
dated January 1994, on which the inspection and installation of
washers, tab washers, and flat washers have been accomplished prior
to the effective date of this AD in accordance with that service
bulletin, and in accordance with the requirements of AD 94-14-06,
amendment 39-8958: Prior to the accumulation of 200 hours time-in-
service or within one year after the effective date of this AD,
whichever occurs first, remove the washers, tab washers, and flat
washers, having part numbers specified in Table 1 of this AD, from
the roller attach bolts of the left and right flaps, and replace
them with new washers, tab washers, and flat washers, having part
numbers specified in Table 2 of this AD, in accordance with Part I
of Raytheon Service Bulletin No. 2522, Revision 1, dated May 1996.
Table 1.--Parts To Be Replaced
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Part Beech Part Number
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Tab Washers.......................... NAS460-616
MS27111-3
168AS-06-02
Flat Washers......................... AN960D616L
Washers.............................. AN960-616
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Table 2.--New Replacement Parts
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Part Beech Part Number
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Tab Washers.......................... 45A16122-37
Flat Washers......................... AN960D616L
Washers.............................. AN960-616
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(b) For all other airplanes not subject to paragraph (a) of this
AD: Prior to the accumulation of 200 hours time-in-service after the
effective date of this AD, or within one year after the effective
date of this AD, whichever occurs first, accomplish the actions
specified in paragraphs (b) (1) and (b) (2) of this AD:
(1) Perform an inspection of the roller attach nuts and bolts
for the flaps to detect discrepancies (i.e., flattened, worn or
damaged threads, damaged keway of bolts, etc.), in accordance with
Part II of Raytheon Service Bulletin No. 2522, Revision 1, dated May
1996. If any discrepancies are found, prior to further flight,
replace the discrepant parts with new or serviceable parts, in
accordance with the service bulletin. And
(2) Remove the washers, tab washers, and flat washers from the
roller attachment bolts of the left and right flaps, and replace
them with new washers, tab washers, and flat washers that have part
numbers specified in Table 2 of this AD, in accordance with Part I
of Raytheon Service Bulletin No. 2522, Revision 1, dated May 1996.
(c) As of the effective date of this AD, no person shall install
on any airplane any tab washer for the roller attach bolt, having
Beech part number 168AS-06-2, NAS460-616, or MS27111-3.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Wichita Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate. Operators shall
submit their requests through an appropriate FAA Principal
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) 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.
Issued in Renton, Washington, on September 23, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-24889 Filed 9-27-96; 8:45 am]
BILLING CODE 4910-13-U