[Federal Register Volume 67, Number 78 (Tuesday, April 23, 2002)]
[Rules and Regulations]
[Pages 19646-19650]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-9729]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-58-AD; Amendment 39-12726; AD 2001-25-52]
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; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2001-25-52, which was sent 
previously to all known U.S. owners and operators of Schweizer Aircraft 
Corporation (Schweizer) Model 269A, 269A-1, 269B, 269C, and TH-55A 
helicopters by individual letters. This AD supersedes an existing AD 
that requires inspecting and modifying or replacing, if necessary, the 
aluminum end fittings of each tailboom support strut (strut). That AD 
also requires inspecting the tailboom center attach fittings and center 
frame aft cluster fittings for damage, and if damaged parts are found, 
replacing the damaged parts. This AD requires inspecting and replacing, 
if necessary, each strut clevis lug (lug) on each tailboom center frame 
aft cluster fitting (cluster fitting), certain strut assemblies, 
certain tailboom attachments, and certain frame aft cluster fittings. 
Modifying or replacing each strut assembly within a certain time period 
and serializing certain strut assemblies are also required. This AD is 
prompted by an accident in the United Kingdom involving the in-flight 
structural failure of a Schweizer Model 269C helicopter. The actions 
specified by this AD are intended to prevent failure of a lug on a 
cluster fitting, rotation of a tailboom into the main rotor blades, and 
subsequent loss of control of the helicopter.

DATES: Effective May 8, 2002, to all persons except those persons to 
whom it was made immediately effective by Emergency AD 2001-25-52, 
issued on December 14, 2001, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 8, 2002.

[[Page 19647]]

    Comments for inclusion in the Rules Docket must be received on or 
before June 24, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-58-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].
    The applicable service information 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.

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: The FAA issued AD 76-18-01 (41 FR 37093, 
September 2, 1976) on August 23, 1976, which amended AD No. 73-3-1 (38 
FR 2331). AD 76-18-01 required visually inspecting the aluminum end 
fittings of each strut for deformation or damage and dye-penetrant 
inspecting for a crack and, if deformation, damage or a crack is found, 
modifying or replacing the part. Modifying or replacing the parts 
within specified hours time-in-service (TIS) is also required. Also, 
that AD requires inspecting the tailboom center attach fittings and 
center frame aft cluster fittings for damage, and if damaged parts are 
found, replacing the damaged parts.
    Since the issuance of that AD, an accident occurred in the United 
Kingdom involving an in-flight structural failure of a Schweizer Model 
269C helicopter. The Air Accidents Investigation Branch of the United 
Kingdom investigated the accident and recommended that the FAA issue an 
AD requiring certain inspections of the clevis lugs and replacing 
certain cluster fittings. The FAA determined that the unsafe condition 
was due to cracking of the cluster fitting. Therefore, on December 14, 
2001, the FAA issued AD 2001-25-52 to supersede AD 76-18-01. AD 2001-
25-52 retains the inspection, modification and replacement requirements 
of the strut, but adds a requirement to dye-penetrant inspect the lugs 
on both cluster fittings within 10 hours TIS and at specified 
intervals, and, before further flight, replace any cracked cluster 
fitting.
    The FAA has reviewed Schweizer Service Information Notice No. N-
109.2, dated, September 1, 1976, which describes procedures for 
inspecting tailboom support strut aluminum end fittings and replacing 
aluminum end fittings with stainless steel end fittings. The FAA has 
also reviewed Schweizer Service Information Notice No. N-108, dated May 
21, 1973, which describes procedures for serializing the tailboom 
support strut assembly.
    Since the unsafe condition described is likely to exist or develop 
on other Schweizer Model 269A, 269A-1, 269B, 269C, and TH-55A 
helicopters of the same type designs, the FAA issued Emergency AD 2001-
25-52 to prevent failure of a lug on a cluster fitting, rotation of a 
tailboom into the main rotor blades, and subsequent loss of control of 
the helicopter. The AD requires the following:
     Initially and at specified intervals, inspect the lugs on 
both cluster fittings, certain strut assemblies, certain tail boom 
attachments and center frame aft cluster fittings. If damage or a crack 
is found, before further flight replace each damaged or cracked part 
with an airworthy part;
     Modify or replace each strut assembly within the specified 
TIS or one year, whichever occurs first; and
     Serialize certain strut assemblies.
    The actions must be accomplished in accordance with the service 
information notices described previously. The short compliance time 
involved is required because the previously described critical unsafe 
condition can adversely affect the structural integrity of the 
helicopter. Therefore, the actions previously stated are required at 
the specified time intervals, and this AD must be issued immediately.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual letters 
issued on December 14, 2001 to all known U.S. owners and operators of 
Schweizer Model 269A, 269A-1, 269B, 269C, and TH-55A helicopters. These 
conditions still exist, and the AD is hereby published in the Federal 
Register as an amendment to 14 CFR 39.13 to make it effective to all 
persons.
    The FAA estimates that 500 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, and 0.25 work 
hours to serialize the strut assembly. The average labor rate is $60 
per work hour. Required parts will cost approximately $5.00 for each 
fitting inspection, $1635 to replace a cluster fitting, and $1500 to 
modify or replace the strut assembly. Based on these figures, the total 
cost impact of the AD on U.S. operators is estimated to be $283,280 
(assuming 1000 cluster fittings are inspected, 50 cluster fittings are 
replaced, 6 strut assemblies are modified or replaced, and 6 strut 
assemblies are serialized).

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available in the Rules Docket for examination by interested persons. A 
report that summarizes each FAA-public contact concerned with the 
substance of this AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this rule must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-58-AD.'' The postcard will be date 
stamped and returned to the commenter.
    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States,

[[Page 19648]]

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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

    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

    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 adding a new airworthiness directive 
to read as follows:

2001-25-52  Schweizer Aircraft Corporation: Amendment 39-12726. 
Docket No. 2001-SW-58-AD. Supersedes AD 76-18-01, Amendment No. 39-
2707, Docket No. 72-WE-23-AD.

    Applicability: Model 269A, 269A-1, 269B, 269C, and TH-55A 
helicopters, with tailboom support strut (strut) assemblies, part 
number (P/N) 269A2015 or P/N 269A2015-5; tailboom center attach 
fitting, P/N 269A2324; or with a center frame aft cluster fitting, 
P/N 269A2234 or 269A2235, installed, certificated in any category.

    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 (d) 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 strut clevis lug (lug) on a center frame 
aft cluster fitting (cluster fitting), 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 269A2235:
    (1) Using paint remover, remove paint from the lugs on each aft 
cluster fitting. Wash with water and dry.
    (2) Dye-penetrant inspect the lugs on each aft cluster fitting. 
See Figure 1.
    (3) If a crack is found, before further flight, replace the 
cracked cluster fitting with an airworthy cluster fitting. Cluster 
fittings, P/N 269A2234 and 269A2235, are not eligible to replace a 
cracked cluster fitting.

[[Page 19649]]

[GRAPHIC] [TIFF OMITTED] TR23AP02.008

    (b) 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 with accordance 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 
(b)(1)(iii) of this AD.
    (c) For Schweizer Aircraft Corporation Model 269C helicopters, 
within 100 hours TIS, serialize each strut assembly, P/N 269A2015-5 
and 269A2015-11, in accordance with Schweizer Service Information 
Notice No. N-108, dated May 21, 1973.
    (d) 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.

    (e) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where

[[Page 19650]]

the requirements of this AD can be accomplished.
    (f) The inspections and modifications shall be done in 
accordance with Steps II and III of Schweizer Service Information 
Notice No. N-109.2, dated September 1, 1976 and Schweizer Service 
Information Notice No. N-108, dated May 21, 1973, as applicable. 
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.
    (g) This amendment becomes effective on May 8, 2002, to all 
persons except those persons to whom it was made immediately 
effective by Emergency AD 2001-25-52, issued December 14, 2001, 
which contained the requirements of this amendment.

    Issued in Fort Worth, Texas, on April 12, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-9729 Filed 4-22-02; 8:45 am]
BILLING CODE 4910-13-U