[Federal Register Volume 63, Number 156 (Thursday, August 13, 1998)]
[Proposed Rules]
[Pages 43333-43335]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-21658]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-203-AD]
RIN 2120-AA64
Airworthiness Directives; Short Brothers Model SD3-30, SD3-60,
SD3-60 SHERPA, and SD3 SHERPA Series Airplanes; Short Brothers Model
SD3-30 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 SD3-30, SD3-60, SD3-60 SHERPA,
and SD3 SHERPA series airplanes. This proposal would require repetitive
visual inspections of the flap levers and bracket assembly of the inner
flap sub-assembly of the left and right wings to detect certain
discrepancies; and corrective actions, if necessary. This proposal is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified by
the proposed AD are intended to detect and correct failure of the
levers and bracket assembly, which could result in uncommanded
retraction of the inner flap assembly and consequent reduced
controllability of the airplane.
DATES: Comments must be received by September 14, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-203-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 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: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; 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 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 98-NM-203-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. 98-NM-203-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 SD3-30, SD3-60, SD3-60
SHERPA, and SD3 SHERPA series airplanes. The CAA advises that, during
an inspection, evidence of corrosion, cracking, and protective coating
breakdown was detected on the levers and bracket assembly of the inner
flap sub-assembly of the left and right wings. Investigation revealed
that the discrepancies may have been initiated by incorrect rigging of
the flaps. Such discrepancies, if not corrected, could result in
failure of the levers and bracket assembly, which could result in
uncommanded retraction of the inner flap assembly and consequent
reduced controllability of the airplane.
Explanation of Relevant Service Information
Shorts has issued the following service bulletins, all dated
January 14, 1997:
SD360-27-26 (for Model SD3-60 series airplanes);
SD360 Sherpa 27-1 (for Model SD3-60 SHERPA series
airplanes);
SD3 Sherpa 27-2 (for Model SD3 SHERPA series airplanes);
and
SD3-27-36 (for Model SD3-30 series airplanes).
These service bulletins describe procedures for repetitive visual
inspections of the flap levers and bracket assembly of the inner flap
sub-assembly of the left and right wings to detect discrepancies (i.e.,
corrosion, cracking, protective coating breakdown, and inadequate
clearances between the forward face of the lower levers and the
[[Page 43334]]
bracket web); and corrective actions, if necessary. The corrective
actions include renewal of protective coating, removal of corrosion and
cracking within acceptable limits, replacement of discrepant parts with
new parts, and re-rigging of the inner flap system. Accomplishment of
the actions specified in the service bulletins is intended to
adequately address the identified unsafe condition. The CAA classified
these service bulletins as mandatory and issued British airworthiness
directives 008-01-97, 010-01-97, 011-01-97, and 009-01-97 in order to
assure the continued airworthiness of these airplanes in the United
Kingdom.
FAA's Conclusions
These airplane models are manufactured in the United Kingdom and
are type certificated for operation in the United States under the
provisions of section 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 bulletins described previously.
Cost Impact
The FAA estimates that 99 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 5 work
hours per airplane to accomplish the proposed inspection, and that the
average labor rate is $60 per work hour. Based on these figures, the
cost impact of the inspection proposed by this AD on U.S. operators is
estimated to be $29,700, or $300 per airplane, per inspection cycle.
The cost impact figure discussed above is 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 adding the following new
airworthiness directive:
Short Brothers PLC: Docket 98-NM-203-AD.
Applicability: All Model SD3-30, SD3-60, SD3-60 SHERPA, and SD3
SHERPA series airplanes, 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 (b) 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 failure of the levers and bracket assembly, which
could result in uncommanded retraction of the inner flap assembly
and consequent reduced controllability of the airplane:
(a) Within 90 days after the effective date of this AD: Perform
a visual inspection of the levers and bracket assembly of the inner
flap sub-assembly of the left and right wings to detect
discrepancies (i.e., corrosion, cracking, protective coating
breakdown, and inadequate clearances between the forward face of the
lower levers and the bracket web), in accordance with the applicable
Shorts service bulletin specified below, all dated January 14, 1997:
SD360-27-26 (for Model SD3-60 series airplanes);
SD360 Sherpa 27-1 (for Model SD3-60 SHERPA series
airplanes);
SD3 Sherpa 27-2 (for Model SD3 SHERPA series
airplanes); and
SD3-27-36 (for Model SD3-30 series airplanes).
(1) If no discrepancy is detected, repeat the visual inspection
thereafter at intervals not to exceed 4,800 flight hours or 24
months, whichever occurs earlier.
(2) If any discrepancy is detected, prior to further flight,
rework the affected area, and accomplish follow-on corrective
actions, in accordance with the applicable service bulletin.
(i) If the reworked parts remain within the allowable rework
limits specified in the applicable service bulletin, repeat the
visual inspection of the levers and bracket assembly thereafter at
intervals not to exceed 1,200 flight hours or 6 months, whichever
occurs earlier.
(ii) If any reworked part is outside the allowable rework limits
specified in the applicable service bulletin, prior to further
flight, replace the reworked part with a new part. Thereafter,
repeat the inspection at intervals not to exceed 4,800 flight hours
or 24 months, whichever occurs earlier.
(b) 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, International Branch, ANM-116, FAA,
Transport 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, International
Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(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
[[Page 43335]]
a location where the requirements of this AD can be accomplished.
Note 3: The subject of this AD is addressed in British
airworthiness directives 008-01-97, 010-01-97, 011-01-97, and 009-
01-97.
Issued in Renton, Washington, on August 6, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-21658 Filed 8-12-98; 8:45 am]
BILLING CODE 4910-13-P
