Airworthiness Directives; Schweizer Aircraft Corporation Model 269A, 269A-1, 269B, 269C, and TH-55A Helicopters

[Federal Register Volume 69, Number 128 (Tuesday, July 6, 2004)]
[Rules and Regulations]
[Pages 40539-40541]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-15128]



[[Page 40539]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-25-AD; Amendment 39-13709; AD 2003-13-15 R1]
RIN 2120-AA64


Airworthiness Directives; Schweizer Aircraft Corporation Model 
269A, 269A-1, 269B, 269C, and TH-55A Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD), for the specified Schweizer Aircraft Corporation (Schweizer) 
model helicopters, that 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. 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 
amendment requires the same actions as the existing AD, but revises the 
Applicability section of the AD. This amendment is prompted by the 
discovery of an error in the Applicability section of the existing AD. 
The actions specified by this 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: Effective August 10, 2004.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of August 12, 2003 (68 FR 40478, July 8, 2003).

ADDRESSES: The service information referenced in this AD may be 
obtained from Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New 
York 14902. This information may be examined at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort 
Worth, Texas; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at NARA, 
call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

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: A proposal to amend 14 CFR part 39 by 
revising AD 2003-13-15, Amendment 39-13217 (68 FR 40478, July 8, 2003), 
for the specified Schweizer helicopters, was published in the Federal 
Register on February 19, 2004 (69 FR 7710). The action proposed to 
require certified persons to:
    <bullet> 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;
    <bullet> 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;
    <bullet> 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;
    <bullet> Within 100 hours TIS, for Model 269C helicopters, 
serialize each strut assembly, P/N 269A2015-5 and 269A2015-11;
    <bullet> 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
    <bullet> Before further flight, replace any cluster fitting that is 
cracked or has a surface defect beyond rework limits.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    The FAA estimates that 1,000 helicopters of U.S. registry will be 
affected by the AD. It will 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 
will 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 adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
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),

[[Page 40540]]

Amendment 39-13709, to read as follows:

2003-13-15 R1 Schweizer Aircraft Corporation: Amendment 39-13709. 
Docket No. 2002-SW-25-AD. Revises AD 2003-13-15, Amendment 39-13217, 
Docket No. 2002-SW-25-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 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:
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[GRAPHIC] [TIFF OMITTED] TR06JY04.000

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[[Page 40541]]

    (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) 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.
    (i) The inspections, modifications or replacements, and 
serializing shall be done in accordance with Schweizer Service 
Information Notice No. N-109.2, dated September 1, 1976; Schweizer 
Service Information Notice No. N-108, dated May 21, 1973; and 
Schweizer Service Bulletin No. B-277, dated January 25, 2002, as 
applicable. The incorporation by reference of those documents was 
approved previously by the Director of the Federal Register, in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of August 12, 
2003 (68 FR 40478, July 8, 2003). Copies may be obtained from 
Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 
14902. Copies may be inspected at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    (j) This amendment becomes effective on August 10, 2004.

    Issued in Fort Worth, Texas, on June 24, 2004.
Kim Smith,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-15128 Filed 7-2-04; 8:45 am]
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