[Federal Register Volume 64, Number 159 (Wednesday, August 18, 1999)]
[Rules and Regulations]
[Pages 44823-44825]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-21177]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-31-AD; Amendment 39-11258; AD 99-17-10]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) 
applicable to Schweizer Aircraft Corporation (SAC) Model 269A, 269A-1, 
269B, 269C, 269C-1, and 269D helicopters. This action 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 is prompted by 
the discovery of an undersized replacement shaft during routine 
maintenance. The actions specified in this AD are intended to prevent 
failure of the shaft and subsequent loss of control of the helicopter.

DATES: Effective September 2, 1999. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of September 2, 1999. Comments for 
inclusion in the Rules Docket must be received on or before October 18, 
1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

[[Page 44824]]

Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 99-SW-31-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas.
    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 76137; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: George J. Duckett, Aerospace Engineer, 
New York Aircraft Certification Office, FAA, 10 Fifth Street, 3rd 
Floor, Valley Stream, New York 11581, telephone (516) 256-7525, fax 
(516) 568-2716.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD applicable to 
SAC Model 269A, 269A-1, 269B, 269C, 269C-1, and 269D helicopters with 
shaft, part number (P/N) 269A6049-3, installed. The undersized shafts 
were shipped from the factory as spares between September 1 and 
December 1, 1998. This action requires the following inspections and 
replacement:
     Within the next 10 hours time-in-service (TIS) and 
thereafter at intervals not exceeding 10 hours TIS until the next 100-
hour or annual inspection, whichever occurs first, inspect the shaft 
nut, P/N 269A6258, for looseness by using a firm hand pressure. If the 
shaft nut is loose, inspect the shaft for the proper size.
     At the next 100-hour or annual inspection, whichever 
occurs first, inspect the shaft, P/N 269A6049-3, for the proper size.
     Prior to further flight, replace any undersized shaft with 
an airworthy shaft of the proper size.
    This amendment is prompted by the discovery of an undersized 
replacement shaft during routine maintenance. The actions specified in 
this AD are intended to prevent failure of the shaft and subsequent 
loss of control of the helicopter.
    The FAA has reviewed SAC Service Bulletins B-271, DB-007, and C1B-
009, all dated March 12, 1999, which describe procedures for inspecting 
the shaft nut, P/N 269A6258, for looseness by using a firm hand 
pressure and the shaft, P/N 269A6049-3, for proper size.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Model 269A, 269A-1, 269B, 269C, 269C-1, and 
269D helicopters of the same type design, this AD is being issued to 
prevent failure of the shaft and subsequent loss of control of the 
helicopter. This AD requires inspecting the shaft nut, P/N 269A6258, 
for looseness; inspecting the shaft, P/N 269A6049-3, for the proper 
size; and replacing any undersized shaft with an airworthy shaft of the 
proper size. The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability of the helicopter. Therefore, inspecting the shaft nut, 
P/N 269A6528, for looseness is required within the next 10 hours TIS 
and this AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    The FAA estimates that 28 helicopters will be affected by this AD. 
For each helicopter, it will take 0.25 work hour to accomplish the 10-
hour inspection, 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.

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, both before and after the closing date for comments, 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 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. 99-SW-31-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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.

[[Page 44825]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

AD 99-17-10  Schweizer Aircraft Corporation: Amendment 39-11258. 
Docket No. 99-SW-31-AD.

    Applicability: Model 269A, 269A-1, 269B, 269C, 269C-1, and 269D 
helicopters, with a tail rotor swashplate shaft (shaft), part number 
(P/N) 269A6049-3, 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 the shaft and subsequent loss of control 
of the helicopter, accomplish the following:
    (a) Within the next 10 hours time-in-service (TIS) and 
thereafter at intervals not to exceed 10 hours TIS until the next 
100-hour or annual inspection, whichever occurs first, cut the 
lockwire; retract the boot on the pitch control assembly; and 
inspect the shaft nut, P/N 269A6258, for looseness by using a firm 
hand pressure. If the shaft nut is loose and can be turned by hand, 
determine if the shaft, P/N 269A6049-3, is undersized in accordance 
with Part II of Schweizer Aircraft Corp. Service Bulletins B-271, 
DB-007, or C1B-009, all dated March 12, 1999 (SB), as applicable.
    (b) At the next 100-hour or annual inspection, whichever occurs 
first, inspect the shaft, P/N 269A6049-3, for the proper size, in 
accordance with Part II of the applicable SB.
    (c) Prior to further flight, replace any undersized shaft in 
accordance with Part II of the applicable SB.
    (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. 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.

    (e) 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.
    (f) The inspection shall be done in accordance with Schweizer 
Aircraft Corp. Service Bulletins B-271, DB-007, or C1B-009, all 
dated March 12, 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.
    (g) This amendment becomes effective on September 2, 1999.

    Issued in Fort Worth, Texas, on August 4, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-21177 Filed 8-17-99; 8:45 am]
BILLING CODE 4910-13-U