AD 2003-13-15 R1

AD Final Rules - 031315R1.pdf
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AD Number:
2003-13-15 R1
Document Type:
AD Final Rules
Docket Number:
2002-SW-25-AD
Subject Heading:
Airworthiness Directives; Schweizer Aircraft Corporation Model 269A, 269A-1, 269B, 269C, and TH-55A Helicopters
Subject:
Aft cluster fittings
Status:
Current
Citation:
(Federal Register: July 6, 2004 (Volume 69, Number 128))
Citation Publish Date:
07/06/2004
Effective Date:
08/10/2004
Make:
Schweizer Aircraft Corporation
Model:
269A | 269A-1 | 269B | 269C
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
2003-13-15
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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[Federal Register: July 6, 2004 (Volume 69, Number 128)]


[Rules and Regulations]


[Page 40539-40541]


From the Federal Register Online via GPO Access [wais.access.gpo.gov]


[DOCID:fr06jy04-4]


–––––––––––––––––––––––––––––––––––


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.


–––––––––––––––––––––––––––––––––––


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
.
2


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:


•
 
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, part


number (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; and


•
 
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.