[Federal Register Volume 68, Number 38 (Wednesday, February 26, 2003)]
[Proposed Rules]
[Pages 8865-8868]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-4479]



[[Page 8865]]

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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 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: [email protected]. 
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:
    [sbull] 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;
    [sbull] 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.
    [sbull] Within 500 hours TIS or one year, whichever occurs first, 
modify or replace the strut assemblies.
    [sbull] 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:
    [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, 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

[[Page 8866]]

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.
    [sbull] 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:

    Schweizer Aircraft Corporation: Docket No. 2002-SW-25-AD. 
Supersedes AD 2001-25-52, Amendment 39-12726, Docket No. 2001-SW-58-
AD.

    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:

------------------------------------------------------------------------
                                Helicopter serial     With aft cluster
   Helicopter model number           number             fitting, P/N
------------------------------------------------------------------------
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
------------------------------------------------------------------------

    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:

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[GRAPHIC] [TIFF OMITTED] TP26FE03.007

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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 8868]]

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]
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