[Federal Register: February 19, 2004 (Volume 69, Number 33)]
[Proposed Rules]
[Page 7710-7713]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19fe04-17]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-SW-25-AD]
RIN 2120-AA64
Airworthiness Directives; Schweizer Aircraft Corporation Model
269A, 269A-1, 269B, 269C, and TH-55A Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to revise an existing airworthiness
directive (AD) for Schweizer Aircraft Corporation (Schweizer) Model
269A, 269A-1, 269B, 269C, and TH-55A helicopters. That AD currently
requires inspecting the lugs on certain aft cluster fittings and each
aluminum end fitting on certain tailboom struts. Modifying or replacing
each strut assembly within a specified time period and serializing
certain strut assemblies is also required. Additionally, a one-time
inspection and repair, if necessary, of certain additional cluster
fittings, and replacement and modification of certain cluster fittings
within 150 hours time-in-service (TIS) or 6 months, whichever occurs
first, is required. This action would require the same actions as the
existing AD, but would revise the Applicability section of the AD. This
proposal is prompted by the discovery of an error in the Applicability
section of the existing AD. The actions specified by the proposed AD
are intended to prevent failure of a tailboom support strut or a
cluster fitting, which could cause rotation of a tailboom into the main
rotor blades, and subsequent loss of control of the helicopter.
DATES: Comments must be received by April 19, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 2002-SW-25-AD, 2601 Meacham Blvd., Room
663, Fort Worth, Texas 76137. You may also send comments electronically
to the Rules Docket at the following address: 9-asw-adcomments@faa.gov.
Comments may be inspected at the Office of the Regional Counsel between
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: George Duckett, Aviation Safety
Engineer, FAA, New York Aircraft Certification Office, Airframe and
Propulsion Branch, 10 Fifth Street, 3rd Floor, Valley Stream, New York,
telephone (516) 256-7525, fax (516) 568-2716.
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 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 mailed
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made:
``Comments to Docket No. 2002-SW-25-AD.'' The postcard will be date
stamped and returned to the commenter.
Discussion
On June 24, 2003, the FAA issued AD 2003-13-15, Amendment 39-13217
(68 FR 40478, July 8, 2003), to require owners and operators of the
affected helicopters to:
[sbull] Within 10 hours TIS and thereafter at intervals not to exceed
50 hours TIS, dye-penetrant inspect the lugs and replace any cracked
cluster fitting;
[sbull] Within 150 hours TIS or 6 months, whichever occurs first,
replace or modify, using kit, part number (P/N) SA-269K-106-1, each
cluster fitting, P/N 269A2234 and P/N 269A2235;
[sbull] For strut assemblies, P/N 269A2015 or P/N 269A2015-5, at
intervals not to exceed 50 hours TIS, visually inspect the strut
aluminum end fittings for deformation or damage, dye-penetrant inspect
the strut aluminum end fittings for a crack, and replace deformed,
damaged, or cracked parts. Within 500 hours TIS or one year, whichever
occurs first, modify or replace certain part-numbered strut assemblies;
[sbull] Within 100 hours TIS, for Model 269C helicopters, serialize
each strut assembly, P/N 269A2015-5 and 269A2015-11;
[sbull] Within 25 hours TIS or 60 days, whichever occurs first, inspect
and repair cluster fittings, P/N 269A2234-3 and P/N 269A2235-3; and
[sbull] Before further flight, replace any cluster fitting that is
cracked or has a surface defect beyond rework limits.
That action was prompted by the need to expand the applicability to
include certain Hughes-manufactured cluster fittings and to provide a
terminating action for the repetitive dye-penetrant inspections of the
cluster fittings. That condition, if not corrected, could result
[[Page 7711]]
in failure of a tailboom support strut or a cluster fitting, which
could cause rotation of a tailboom into the main rotor blades, and
subsequent loss of control of the helicopter.
Since issuing that AD, we have discovered an error in the
Applicability section that should be changed. The AD currently excepts
helicopters that have Hughes-manufactured cluster fittings installed
and that were originally sold by Hughes after June 1, 1988. We intended
that this exception apply to all cluster fittings, P/N 269A2234-3 or P/
N 269A2235-3, that are installed, regardless of the manufacturer, if
there was written documentation in the aircraft or manufacturer's
records that shows the cluster fitting was originally sold by the
manufacturer after June 1, 1988. Therefore, we are now proposing to
expand the exception to all cluster fittings originally sold after June
1, 1988, regardless of the manufacturer.
The previously described unsafe condition is likely to exist or
develop on other helicopters of the same type designs. Therefore, the
proposed AD would revise AD 2003-13-15 to retain the current
requirements but revise the Applicability to exclude all cluster
fittings with appropriate written documentation showing that the
cluster fitting was originally sold by the manufacturer after June 1,
1988.
The FAA estimates that 1,000 helicopters of U.S. registry would be
affected by the proposed AD. It would take approximately 2.5 work hours
for each dye-penetrant inspection, 12 work hours to replace one cluster
fitting, 4 work hours to modify or replace the strut assembly, 0.25
work hours to serialize the strut assembly, and 16 work hours to modify
a cluster fitting. The average labor rate is $65 per work hour.
Required parts would cost approximately $5 for each fitting inspection,
$1,635 to replace a cluster fitting, $1,500 to modify or replace the
strut assembly, and $1,688 for each cluster fitting modification kit (2
cluster fittings). Based on these figures, the total cost impact of the
AD on U.S. operators is estimated to be $2,369,248 (assuming 2,000
cluster fittings are inspected, 50 cluster fittings are replaced, 6
strut assemblies are modified or replaced, 6 strut assemblies are
serialized, and 1,010 cluster fittings are modified).
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 removing Amendment 39-13217 (68 FR
40478, July 8, 2003), and by adding a new airworthiness directive (AD),
to read as follows:
Schweizer Aircraft Corporation: Docket No. 2002-SW-25-AD. Revises AD
2003-13-15, Amendment 39-13217.
Applicability: Model 269A, 269A-1, 269B, 269C, and TH-55A
helicopters, certificated in any category, with a tailboom support
strut (strut) assembly, part number (P/N) 269A2015 or 269A2015-5; or
with a center frame aft cluster fitting, P/N 269A2234 or 269A2235,
and an aft cluster fitting listed in the following table:
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Helicopter model number Helicopter serial number With aft cluster fitting, P/N
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Model 269C......................... 0570 through 1165.......... 269A2234-3.
Model 269C......................... 0500 through 1165.......... 269A2235-3.
Model 269A, A-1, B, or C, or TH-55A All........................ 269A2234-3 or 269A2235-3.
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Exception: For the Model 269A, A-1, B, or C or TH-55A helicopters
with cluster fittings, P/N 269A2234-3 or P/N 269A2235-3, installed,
if there is written documentation in the aircraft or manufacturer's
records that shows the cluster fitting was originally sold by the
manufacturer after June 1, 1988, the requirements of this AD are not
applicable.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of a tailboom support strut or lug on a
cluster fitting, which could cause rotation of a tailboom into the
main rotor blades, and subsequent loss of control of the helicopter,
accomplish the following:
(a) Within 10 hours time-in-service (TIS), and thereafter at
intervals not to exceed 50 hours TIS, for helicopters with cluster
fittings, P/N 269A2234 or P/N 269A2235:
(1) Using paint remover, remove paint from the lugs on each
cluster fitting. Wash with water and dry. The tailboom support strut
must be removed prior to the paint stripping.
(2) Dye-penetrant inspect the lugs on each cluster fitting. See
the following Figure 1:
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[[Page 7712]]
[GRAPHIC] [TIFF OMITTED] TP19FE04.000
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(3) If a crack is found, before further flight, replace the
cracked cluster fitting with an airworthy cluster fitting.
(b) Cluster fittings, P/N 269A2234 and P/N 269A2235, that have
NOT been modified with Kit P/N SA-269K-106-1, are NOT eligible
replacement parts.
(c) Within 150 hours TIS or 6 months, whichever occurs first,
replace each cluster fitting, P/N 269A2234 and P/N 269A2235, with an
airworthy cluster fitting or modify each cluster fitting, P/N
269A2234 and P/N 269A2235, with Kit, P/N SA-269K-106-1. Installing
the kit is terminating action for the 50-hour TIS repetitive dye-
penetrant inspection for these cluster fittings. Broken or cracked
cluster fittings are not eligible for the kit modification.
(d) For helicopters with strut assemblies, P/N 269A2015 or
269A2015-5, accomplish the following:
(1) At intervals not to exceed 50 hours TIS:
(i) Remove the strut assemblies, P/N 269A2015 or P/N 269A2015-5.
(ii) Visually inspect the strut aluminum end fittings for
deformation or damage and dye-penetrant inspect the strut aluminum
end fittings for a crack in accordance with Step II of Schweizer
Service Information Notice No. N-109.2, dated September 1, 1976 (SIN
N-109.2).
(iii) If deformation, damage, or a crack is found, before
further flight, modify the strut assemblies by replacing the
aluminum end fittings with stainless steel end fittings, P/N
269A2017-3 and -5, and attach bolts in accordance with Step III of
SIN N-109.2; or replace each strut assembly P/N 269A2015 with P/N
269A2015-9, and replace each strut assembly P/N 269A2015-5 with P/N
269A2015-11.
(2) Within 500 hours TIS or one year, whichever occurs first,
modify or replace the strut assemblies in accordance with paragraph
(d)(1)(iii) of this AD.
(e) For the Model 269C helicopters, within 100 hours TIS,
serialize each strut assembly, P/N 269A2015-5 and P/N 269A2015-11,
in accordance with Schweizer Service Information Notice No. N-108,
dated May 21, 1973.
(f) Within 25 hours TIS or 60 days, whichever occurs first, for
cluster fittings, P/N 269A2234-3 and P/N 269A2235-3, perform a one-
time inspection and repair, if required, in accordance with
Procedures, Part II of Schweizer Service Bulletin No. B-277, dated
January 25, 2002.
(g) Before further flight, replace any cluster fitting that is
cracked or has surface defects
[[Page 7713]]
beyond rework limits with an airworthy cluster fitting.
(h) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, New York Aircraft Certification Office (NYACO),
Engine and Propeller Directorate, FAA, for information about
previously approved alternative methods of compliance.
Issued in Fort Worth, Texas, on February 9, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-3495 Filed 2-18-04; 8:45 am]
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