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

[Federal Register Volume 68, Number 130 (Tuesday, July 8, 2003)]
[Rules and Regulations]
[Pages 40478-40481]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-16685]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-SW-25-AD; Amendment 39-13217; AD 2003-13-15]
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 supersedes an existing airworthiness directive 
(AD), applicable to Schweizer Aircraft Corporation (Schweizer) Model 
269A, 269A-1, 269B, 269C, and TH-55A 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 by the existing AD. This 
amendment requires the same actions as the existing AD, and also 
requires 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. This amendment 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 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 12, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 12, 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 Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

[[Page 40479]]


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 
superseding AD 2001-25-52, Amendment 39-12726 (67 FR 19646, April 23, 
2002), for Schweizer Model 269A, 269A-1, 269B, 269C, and TH-55A 
helicopters, was published in the Federal Register on February 26, 2003 
(68 FR 8865). That action proposed to require:
    [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.
    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.
    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. The 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. However, 
for clarity and consistency in this final rule, we have retained the 
language of the NPRM regarding that material.
    The FAA estimates that 1,000 helicopters of U.S. registry will be 
affected by this 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 $60 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 
fittings). Based on these figures, the total cost impact of the 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 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 39-12726 (67 FR 
19646, April 23, 2002), and by adding a new airworthiness directive 
(AD), Amendment 39-13217, to read as follows:

2003-13-15 Schweizer Aircraft Corporation: Amendment 39-13217. 
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

[[Page 40480]]

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] TR08JY03.014

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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

[[Page 40481]]

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.
    (j) The inspections, modifications, replacements and 
serializations 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. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. 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 Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (k) This amendment becomes effective on August 12, 2003.

    Issued in Fort Worth, Texas, on June 24, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-16685 Filed 7-7-03; 8:45 am]
BILLING CODE 4910-13-P

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