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 SERIAL WITH AFT CLUSTER
HELICOPTER MODEL NUMBER NUMBER 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 All................. 269A2234-3 or
TH-55A. 269A2235-3
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EXCEPTION: For the Model 269A, A-1, B, or C or TH-55A helicopters with
Hughes-manufactured 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 Hughes after June 1, 1988, the requirements of this AD are not
applicable.
NOTE 1: This AD applies to each helicopter identified in the preceding
applicability provision, regardless of whether it has been otherwise
modified, altered, or repaired in the area subject to the requirements of
this AD. For helicopters 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 (h) 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 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:
ILLUSTRATION (Figure 1)
(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 beyond rework limits with an airworthy
cluster fitting.
(h) 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, New York Aircraft Certification Office
(NYACO), FAA. Operators shall submit their requests through an FAA
Principal Maintenance Inspector, who may concur or comment and then
send it to the Manager, NYACO.
NOTE 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the NYACO.
(i) Special flight permits may be issued in accordance with 14 CFR 21.197
and 21.199 to operate the helicopter to a location where the
requirements of this AD can be accomplished.
Issued in Fort Worth, Texas, on February 18, 2003. Eric D. Bries, Manager,
Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-4479 Filed 2-25-03; 8:45 am]
DATES: Comments must be received on or before April 28, 2003.
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 the supersedure of an existing
airworthiness directive (AD) that applies to 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 are also required by the
existing AD. This proposed AD would require the same actions as the
existing AD, would require a one-time inspection and repair, if necessary,
of certain additional cluster fittings, and would require replacement and
modification of certain cluster fittings within 150 hours time-in-service
(TIS) or 6 months, whichever occurs first. This proposal is 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. 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 on or before April 28, 2003.
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
will be considered before taking action on the proposed rule. The
proposals contained in this document 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 April 12, 2002, the FAA issued AD 2001-25-52, Amendment 39-12726
(67 FR 19646, April 23, 2002), to require the following:
• Within 10 hours TIS and thereafter at intervals not to exceed 50
hours TIS, dye-penetrant inspect and replace, if necessary, each
cluster fitting, part number (P/N) 269A2234 and P/N 269A2235;
• 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 the strut assemblies.
• Within 100 hours TIS, for Model 269C helicopters, serialize each
strut assembly, P/N 269A2015-5 and 269A2015-11.
That action was prompted by an accident in the United Kingdom
involving the in-flight structural failure of a Model 269C helicopter.
The requirements of that AD are intended to prevent failure of a lug
on a cluster fitting, which could result in rotation of a tailboom
into the main rotor blades, and subsequent loss of control of the
helicopter. The existing AD, which superseded AD 76-18-01 (41 FR
37093, September 2, 1976), includes a reference to inspecting the
center attachment fitting. However, AD 93-21-03 (58 FR 59944, November
12, 1993), Docket 91-ASW-11, addressed the unsafe conditions of the
center attachment fitting and it is unnecessary to further address
those issues in this proposed AD.
Since the issuance of the existing AD, the FAA has determined that the
pool of cluster fittings that needs inspecting should be expanded to
include certain Hughes-manufactured cluster fittings that were
inadvertently omitted from the applicability of the existing AD
because of the failure to include Hughes-manufactured P/N's, 269A2234
-3 and 269A2235-3, in the applicability. Also, the manufacturer has
completed the development of a modification kit for the cluster
fitting that can serve as a terminating action for the repetitive 50
-hour TIS dye- penetrant inspection.
The unsafe condition described previously is likely to exist or
develop on other helicopters of the same type designs. Therefore, the
proposed AD would supersede AD 2001-25-52 to require the following:
• 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.
• Within 150 hours TIS or 6 months, whichever occurs first, replace or
modify, using kit, P/N SA-269K-106-1, each cluster fitting, P/N
269A2234 and P/N 269A2235.
• 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.
• Within 100 hours TIS, for Model 269C helicopters, serialize each
strut assembly, P/N 269A2015-5 and 269A2015-11. • Within 25 hours TIS
or 60 days, whichever occurs first, inspect and repair cluster
fittings, P/N 269A2234-3 and P/N 269A2235-3.
• Before further flight, replace any cluster fitting that is cracked
or has a surface defect beyond rework limits.
The FAA estimates that 1,000 helicopters of U.S. registry would be
affected by this 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 $60 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 fittings). Based on these figures, the total cost
impact of the proposed AD on U.S. operators is estimated to be
$2,260,320 (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 39-12726 (67 FR
19646, April 23, 2002), and by adding a new airworthiness directive
(AD), to read as follows: