[Federal Register Volume 65, Number 174 (Thursday, September 7, 2000)]
[Proposed Rules]
[Pages 54182-54184]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 00-22910]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 65, No. 174 / Thursday, September 7, 2000 /
Proposed Rules
[[Page 54182]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NM-65-AD]
RIN 2120-AA64
Airworthiness Directives; Cessna Model 500 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Cessna Model 500 series
airplanes. This proposal would require inspection of the piston housing
for an ``SB'' impression stamp; a one-time inspection of the brake
assembly to detect cracked or broken brake stator disks; and
replacement of the brake assembly with a new or serviceable assembly,
if necessary. The proposal is prompted by several reports of wheel
lockups that appear to be caused by cracked or broken brake stator
disks becoming jammed in the brake assembly and preventing rotation.
Such jamming of the brake assembly may result in reduced directional
control or braking performance during landing.
DATES: Comments must be received by October 23, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2000-NM-65-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232
or sent via the Internet using the following address: 9-anm-
nprmcomment@faa.gov. Comments sent via fax or the Internet must contain
``Docket No. 2000-NM-65-AD'' in the subject line and need not be
submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 for windows or
ASCI II text.
The service information referenced in the proposed rule may be
obtained from Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas
67277. This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington, or at the FAA,
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100,
Mid-Continent Airport, Wichita, Kansas 67209.
FOR FURTHER INFORMATION CONTACT: Shane Bertish, Aerospace Engineer,
Systems and Propulsion Branch, ACE-116W, Wichita Aircraft Certification
Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita,
Kansas 67209; telephone (316) 946-4156; 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.
Submit comments using the following format:
Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
For each issue, state what specific change to the proposed
AD is being requested.
Include justification (e.g., reasons or data) for each
request.
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 2000-NM-65-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-114, Attention: Rules
Docket No. 2000-NM-65-AD, 1601 Lind Avenue SW., Renton, Washington
98055-4056.
Discussion
The FAA has received reports of wheel lockups after release of
brakes following landing. The lockups adversely affect braking
performance and directional control and appear to be associated with
cracks in the brake stator disks. If multiple cracks extend completely
through the stator, a piece of the disk may break loose and slip down,
jamming the wheel/tire assembly. If not corrected, this condition could
result in the wheel/tire assembly becoming locked in place and
consequent reduced directional control or braking performance during
landing.
Explanation of Relevant Service Information
The FAA has reviewed and approved Cessna Service Bulletin SB500-32-
47, dated February 22, 2000, which transmits BFGoodrich Service
Bulletin 2-1530-32-2, Revision No. 1, dated February 3, 2000, and
Cessna Service Bulletins SB500-32-48 and SB550-32-41, both dated
February 22, 2000, which transmit BFGoodrich Service Bulletin 2-1528-
32-2, Revision No. 1, dated February 3, 2000.
BFGoodrich Service Bulletin 2-1528-32-2, Revision 1 applies to
airplanes equipped with BFGoodrich brake assembly part number P/N 2-
1528-6, and Service Bulletin 2-1530-32-2, Revision 1 applies to
airplanes equipped with BFGoodrich brake assembly P/N 2-1530-4. These
service bulletins describe procedures for inspection for certain
letters impression-stamped on the piston housing or the stator disks;
inspection of the brake
[[Page 54183]]
assembly for cracked or broken stator disks, if no such impression
stamps are found; and replacement of the brake assembly with a new or
serviceable brake assembly.
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 require accomplishment of the actions specified in
the service bulletins described previously.
Cost Impact
There are approximately 370 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 259 airplanes in the U.S.
registry would be affected by this proposed AD, that the average labor
rate is $60 per work hour, and that it would take up to 1 work hour per
airplane to accomplish the proposed inspection if the inspection were
done at the time of a tire change and up to 4 work hours per airplane
if the inspection were done at a different time. Based on these
figures, the cost impact of the proposed AD on U.S. operators is
estimated to be $15,540, or $60 per airplane, for inspections of the
brake assembly done at the time of a tire change and up to $62,160, or
$240 per airplane, for inspections done at a different time.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
proposed AD and that no operator would accomplish those actions in the
future if this proposed AD were not adopted.
The cost impact figures discussed in AD rulemaking actions
represent only the time necessary to perform the specific actions
actually required by the AD. These figures typically do not include
incidental costs, such as the time required to gain access and close
up, planning time, or time necessitated by other administrative
actions.
Regulatory Impact
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 proposal would not have federalism implications
under Executive Order 13132.
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 adding the following new
airworthiness directive:
Cessna Airplane Company: Docket 2000-NM-65-AD.
Applicability: Model 500 and 501 series airplanes, serial
numbers 0001 through 0689 inclusive, and Model 550 and 551 series
airplanes, serial numbers 0002 through 0733 inclusive; certificated
in any category; equipped with BFGoodrich brake assembly part number
(P/N) 2-1528-6 or 2-1530-4.
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 (c) 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 jamming of the wheel/tire assembly, which could
result in a loss of directional control or braking performance upon
landing, accomplish the following:
Inspection
(a) Within the next 50 landings or 90 days after the effective
date of this AD, whichever occurs first, inspect the brake assembly
for an ``SB'' impression stamped on the piston housing, as shown in
Figure 1 of BFGoodrich Service Bulletin 2-1528-32-2, Revision 1 (for
airplanes equipped with BFGoodrich brake assembly P/N 2-1528-6) or
Service Bulletin 2-1530-32-2, Revision 1 (for airplanes equipped
with BFGoodrich brake assembly P/N 2-1530-4), both dated February 3,
2000, as applicable. If an ``SB'' is impression-stamped on the
piston housing, no further action is required by this AD.
(b) Within the next 50 landings or 90 days after the effective
date of this AD, whichever occurs first, inspect the stator disks
for a CHG AI or a CHG B or higher letter impression-stamped on the
disk, in accordance with BFGoodrich Service Bulletin 2-1528-32-2,
Revision 1 (for airplanes equipped with BFGoodrich bake assembly P/N
2-1528-6) or Service Bulletin 2-1530-32-2, Revision 1 (for airplanes
equipped with BF Goodrich brake assembly P/N 2-1530-4), both dated
February 3, 2000, as applicable. Unless both stator disks are so
marked, perform paragraph (b)(1).
(1) When the brake assembly has accumulated 376 total landings
since its installation or within 50 landings on the airplane after
the effective date of this AD, whichever occurs later, perform a
detailed visual inspection for cracked or broken disks in accordance
with the applicable service bulletin.
(i) If no cracked or broken stator disks are found, the brake
assembly can be re-assembled and used until a total of 700 landings
are accumulated on the brake assembly at which time the brake
assembly must be removed and replaced with a new or serviceable
brake assembly.
(ii) If any cracked or broken stator disk is found, prior to
further flight, the brake assembly must be replaced with a new or
serviceable brake assembly.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
(2) When the brake assembly has accumulated 700 total landings
since its installation or within 50 landings on the airplane after
the effective date of this AD, whichever occurs later, replace the
brake assembly with a new or serviceable brake assembly, in
accordance with the applicable service bulletin.
Alternative Method of Compliance
(c) 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. Operators shall submit their requests through
[[Page 54184]]
an appropriate FAA Principal Maintenance Inspector, who may add
comments and then send it to the Manager, Wichita ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
Special Flight Permits
(d) 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 August 31, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 00-22910 Filed 9-6-00; 8:45 am]
BILLING CODE 4910-13-P