[Federal Register: April 22, 2004 (Volume 69, Number 78)]
[Proposed Rules]
[Page 21766-21768]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22ap04-22]
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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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[[Page 21766]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-236-AD]
RIN 2120-AA64
Airworthiness Directives; Short Brothers Model SD3-60 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 all Short Brothers Model SD3-60
series airplanes. This proposal would require inspection of the welded
joints of the balance weight brackets for the left and right elevator
trim tabs for cracking; repetitive inspections, as applicable; and
corrective actions including the eventual replacement of all brackets,
which would constitute terminating action for the repetitive
inspections. This action is necessary to prevent the loss of the
balance weight for the elevator trim tab, which could result in
incorrect trim during takeoff and landing, and reduced controllability
of the airplane. This action is intended to address the identified
unsafe condition.
DATES: Comments must be received by May 24, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-236-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.
Comments may also be sent via the Internet using the following address:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-236-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 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Short Brothers, Airworthiness & Engineering Quality, P.O.
Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. This
information may be examined at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
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 action 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 action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-236-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. 2003-NM-236-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, notified the FAA that an unsafe
condition may exist on all Short Brothers Model SD3-60 series
airplanes. The CAA advises that, on one affected airplane, the balance
weight assembly for an elevator trim tab detached during landing.
Subsequent investigation showed that the failure was caused by fatigue
cracking emanating from the weld of the balance weight bracket. This
condition, if not corrected, could result in the loss of the balance
weight for the elevator trim tab, which could cause incorrect trim
during takeoff and landing, and reduced controllability of the
airplane.
Explanation of Relevant Service Information
Shorts has issued Short Brothers Service Bulletin SD360-55-20,
dated June 26, 2003, which describes procedures for performing a dye
penetrant inspection for cracking in the welded joints of the balance
weight brackets for the left and right elevator trim tabs. Depending on
the results of the dye penetrant inspection, the total number of flight
hours accumulated on the airplane and/or the brackets, and the length
of any crack, the service bulletin describes procedures for further
investigative and corrective actions. These investigative and
corrective actions include refitting the balance weights, performing
repetitive inspections, repairing the bracket (including a further dye
penetrant inspection), and/or replacing the bracket with a new or
serviceable bracket, as
[[Page 21767]]
applicable. The service bulletin gives compliance times for eventual
replacement of all brackets when they reach their life limits. This
service bulletin permits further flight with brackets having a cracked
welded joint, within certain limits.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition. The CAA
classified this service bulletin as mandatory and issued British
airworthiness directive 009-06-2003 to ensure the continued
airworthiness of these airplanes in the United Kingdom.
FAA's Conclusions
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the CAA, reviewed all available information, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require accomplishment of
the actions specified in the service bulletin described previously,
except as discussed below.
Differences Between the Proposed AD and the Service Bulletin
Unlike the procedures described in Short Brothers Service Bulletin
SD360-55-20, dated June 26, 2003, this proposed AD would not permit
further flight if cracks of any length are detected in the welded
joints of the balance weight brackets. We have determined that, because
of the safety implications and consequences associated with such
cracking, any bracket with a cracked welded joint must be repaired or
replaced before further flight.
The service bulletin specifies that operators may contact the
manufacturer for disposition of certain conditions when refitting
balance weights; in those conditions; however, this proposed AD would
require operators to obtain further disposition instructions from the
FAA or the CAA (or its delegated agent).
Cost Impact
The FAA estimates that 42 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 12 work
hours per airplane to accomplish the proposed inspections, and that the
average labor rate is $65 per work hour. Based on these figures, the
cost impact of this proposed action on U.S. operators is estimated to
be $32,760, or $780 per airplane, per inspection cycle.
It would take approximately 8 hours per airplane to accomplish the
proposed replacement of the brackets. Required parts would cost
approximately $632 per airplane. Based on these figures, the cost
impact of this proposed action on U.S. operators is estimated to be
$48,384, or $1,152 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. 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:
Short Brothers PLC: Docket 2003-NM-236-AD.
Applicability: All Model SD3-60 series airplanes, certificated
in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the loss of the balance weight for the elevator trim
tab, which could result in incorrect trim during takeoff and
landing, and reduced controllability of the airplane, accomplish the
following:
Service Bulletin Reference
(a) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Short Brothers Service Bulletin
SD360-55-20, dated June 26, 2003.
Initial Inspection
(b) Within 2 months after the effective date of this AD: Do a
dye penetrant inspection for cracking in the welded joints of the
balance weight brackets for the left and right elevator trim tabs,
in accordance with the service bulletin.
Investigative and Corrective Actions if No Cracking Is Found
(c) If no cracking is found during the inspection required by
paragraph (b) of this AD, do the actions required by paragraphs
(c)(1) and (c)(2) of this AD at the applicable compliance times.
(1) Repeat the inspection required by paragraph (b) of this AD
at intervals not to exceed 4,800 flight hours until the bracket is
replaced per paragraph (c)(2) or (d) of this AD.
(2) Prior to the accumulation of 28,800 total flight hours, or
within 6 months after the effective date of this AD, whichever
occurs later: Replace any bracket that has not been replaced per
paragraph (d) of this AD with a new bracket or with a serviceable
bracket that has been inspected in accordance with paragraph (b) of
this AD. Replace in accordance with the service bulletin.
Replacement of the brackets constitutes terminating action for the
repetitive inspections required by paragraph (c)(1) of this AD.
[[Page 21768]]
Corrective Actions if Any Crack Is Found
(d) If any crack is found during any inspection required by
paragraph (b) or (c) of this AD: Before further flight, accomplish
the applicable action in paragraph (d)(1) or (d)(2) of this AD in
accordance with the service bulletin.
(1) For airplanes that have accumulated less than 28,800 flight
hours and on which all cracks on brackets are less than 0.25 inch in
length: Repair the affected bracket in accordance with Part B of the
service bulletin (including the additional dye penetrant inspection
of the repaired welded joint) and repeat the inspection required by
paragraph (b) of this AD at intervals not to exceed 4,800 flight
hours; or replace the bracket in accordance with paragraph (d)(2) of
this AD. Replacement of the bracket constitutes terminating action
for the repetitive inspections.
(2) For any airplane on which any crack on a bracket is 0.25
inch in length or greater, and for any airplane that has accumulated
28,800 flight hours or more on which any crack of any length is
found on a bracket: Replace the affected bracket with a new bracket
or with a serviceable bracket that has been inspected in accordance
with paragraph (b) of this AD. Replacement of the bracket
constitutes terminating action for the repetitive inspections
required by paragraph (d)(1) of this AD.
Refitting
(e) Before further flight following any inspection per
paragraphs (b) or (c) of this AD; or before further flight following
repair or replacement of a bracket per paragraphs (c)(2) or (d) of
this AD: Refit the balance weights, covers, and trim tabs, in
accordance with the service bulletin. Where the service bulletin
specifies to contact the manufacturer for disposition of certain
conditions while refitting, obtain further disposition instructions
from the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate; or the Civil Aviation Authority (CAA) (or its
delegated agent).
Parts Installation
(f) As of the effective date of this AD, no person may install
on any airplane a balance weight bracket unless the welded joint has
been inspected in accordance with paragraph (b) of this AD.
Alternative Methods of Compliance
(g) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, is authorized to approve alternative methods of
compliance for this AD.
Note 1: The subject of this AD is addressed in British
airworthiness directive 009-06-2003.
Issued in Renton, Washington, on April 15, 2004.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-9110 Filed 4-21-04; 8:45 am]
BILLING CODE 4910-13-P