[Federal Register Volume 65, Number 158 (Tuesday, August 15, 2000)]
[Rules and Regulations]
[Pages 49732-49734]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-20405]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-57-AD; Amendment 39-11859; AD 2000-16-05]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) that applies to Schweizer Aircraft Corporation (Schweizer) Model 
269A, 269A-1, 269B, 269C, 269C-1, 269D helicopters. That AD requires 
inspecting the tail rotor swashplate shaft (shaft) nut for looseness 
and, if loose, inspecting the shaft for proper size; subsequently 
inspecting the shafts not previously inspected; and replacing any 
undersized shaft prior to further flight. This amendment reduces the 
applicability by specifying certain serial number tail rotor pitch 
control (pitch control) assemblies and shipping dates but adds the 
Schweizer Model TH-55A helicopter to the applicability. This amendment 
is prompted by the discovery of an undersized replacement shaft during 
routine maintenance. The actions specified by this AD are intended to 
prevent failure of the shaft, loss of the tail rotor, and subsequent 
loss of control of the helicopter.

DATES: Effective September 19, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 19, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained

[[Page 49733]]

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 
11581, telephone (516) 256-7525, fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 99-17-10, 
Amendment 39-11258 (64 FR 44823, August 18, 1999), which applies to 
Schweizer Model 269A, 269A-1, 269B, 269C, 269C-1, 269D, and TH-55A 
helicopters, was published in the Federal Register on May 9, 2000 (65 
FR 26781). That action proposed to require inspecting the shaft nut, 
part number (P/N) 269A6258, for looseness; inspecting the shaft, P/N 
269A6049-3, for proper size; and replacing any undersized shaft with an 
airworthy shaft of the proper size for helicopters with equipment 
installed as follows:
     Shaft, P/N 269A6049-3, shipped from the factory between 
September 1 and December 1, 1998, and installed after the helicopter 
was manufactured, or
     Pitch control assembly, P/N 269A6050-5, with serial number 
with an ``S'' prefix and number 1047 through 1061.
    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 28 helicopters of U.S. registry will be 
affected by this AD. For each helicopter, it will take approximately 
0.25 work hours to accomplish the 10-hour inspection and 3.6 work hours 
to accomplish the inspection and replacement, if necessary, at the 100-
hour or annual inspection interval. The average labor rate is $60 per 
work hour. Required parts will cost approximately $1400 per helicopter. 
Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $45,668.
    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

    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 removing Amendment 39-11258 (64 FR 
44823, August 18, 1999), and by adding a new airworthiness directive 
(AD), Amendment 39-11859, to read as follows:

2000-16-05 Schweizer Aircraft Corporation: Amendment 39-11859. 
Docket No. 99-SW-57-AD. Supersedes AD 99-17-10, Amendment 39-11258, 
Docket No. 99-SW-31-AD.

    Applicability: Model 269A, 269A-1, 269B, 269C, 269C-1, 269D and 
TH-55A helicopters, with a tail rotor swashplate shaft (shaft), part 
number (P/N) 269A6049-3, or a tail rotor pitch control assembly 
(pitch control), P/N 269A6050-5, with a serial number (S/N) with an 
``S'' prefix and number 1047 through 1061, 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 (c) 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 the shaft, loss of the tail rotor, and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Within 10 hours time-in-service (TIS);
    (1) Determine whether the factory-installed shaft, part number 
(P/N) 269A6049-3, has been replaced with a shaft shipped from the 
factory between September 1 and December 1, 1998, inclusive, or if a 
pitch control, P/N 269A6050-5, with a S/N with an ``S'' prefix and 
numbers 1047 through 1061 is installed.
    (2) If the factory ship date for a replacement shaft cannot be 
positively determined, if the shipping date was between September 1 
and December 1, 1998, inclusive, or if the pitch control S/N has an 
``S'' prefix and number 1047 through 1061,
    (i) Before further flight and thereafter at intervals not to 
exceed 10 hours TIS, accomplish ``Procedure, Part I,'' of Schweizer 
Service Bulletins B-271.1 for Models 269A, 269A-1, 269B, 269C and 
TH-55A helicopters; C1B-009.1 for the Model 269C-1, or DB-007.1 for 
the Model 269D, all dated October 14, 1999 (SB), as applicable.
    (ii) At the next scheduled 100-hour or annual inspection, 
whichever occurs first, accomplish Part II, paragraphs a. through 
d., of the applicable SB. Shafts not meeting the requirements of 
paragraph d. of the applicable SB must be replaced with an airworthy 
shaft prior to further flight.
    (b) Before installing a replacement shaft, determine the date 
the shaft was shipped from the factory. If the date was between 
September 1 and December 1, 1998, inclusive, or cannot be 
determined, accomplish the inspections required by Part II, 
paragraph d., of the applicable SB prior to installation. Replace 
any unairworthy shaft with an airworthy shaft.
    (c) 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. Operators shall submit their requests through an FAA 
Principal Maintenance Inspector, who may concur or comment and then 
send it to the Manager, New York Aircraft Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the New York Aircraft Certification Office.


[[Page 49734]]


    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (e) The inspections and modifications shall be done in 
accordance with ``Procedure, Parts I and II,'' paragraphs a. through 
d., of Schweizer Service Bulletins B-271.1, C1B-009.1, or DB-007.1, 
all dated October 14, 1999, 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.
    (f) This amendment becomes effective on September 19, 2000.

    Issued in Fort Worth, Texas, on August 2, 2000.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-20405 Filed 8-14-00; 8:45 am]
BILLING CODE 4910-13-U