[Federal Register Volume 69, Number 33 (Thursday, February 19, 2004)]
[Proposed Rules]
[Pages 7710-7713]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-3495]


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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: [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, 
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
----------------------------------------------------------------------------------------------------------------
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:
BILLING CODE: 4910-13-P

[[Page 7712]]

[GRAPHIC] [TIFF OMITTED] TP19FE04.000

BILLING CODE: 4910-13-C
    (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]
BILLING CODE 4910-13-P