[Federal Register Volume 60, Number 198 (Friday, October 13, 1995)]
[Rules and Regulations]
[Pages 53265-53266]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25330]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-SW-02-AD; Amendment 39-9387; AD 95-21-02]
Airworthiness Directives; Schweizer Aircraft Corporation and
Hughes Helicopters, Inc. 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 and Hughes
Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A
helicopters with certain main rotor (M/R) drive shafts installed, that
currently requires a one-time radiographic inspection or other non-
destructive inspection of certain M/R drive shafts for cracks,
distortion, corrosion, or other surface damage, at specified time
intervals or upon the occurrence of specified conditions. This
amendment requires the same inspections as the previous AD, but expands
the applicability of certain inspections to additional models of the
affected helicopters, and excludes certain M/R drive shafts from
certain inspections. This amendment is prompted by a reevaluation as a
result of a comment to the previous AD suggesting the need to expand
the applicability of certain inspections to additional models of the
affected helicopters and to exclude certain M/R drive shafts from
certain inspections. The actions specified by this AD are intended to
prevent structural failure of the M/R drive shaft, separation of the M/
R from the helicopter, and subsequent loss of control of the
helicopter.
DATES: Effective November 17, 1995.
The incorporation by reference of certain publications listed in
the regulations was previously approved by the Director of the Federal
Register as of October 29, 1993 (58 FR 53120, October 14, 1993).
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
Assistant Chief Counsel, 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: Mr. Raymond J. O'Neill, Aerospace
Engineer, FAA, New York Aircraft Certification Office, New England
Region, 10 5th Street, Valley Stream, New York 11581, telephone (516)
256-7505, fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 93-14-06,
Amendment 39-8630 (58 FR 53120, October 14, 1993), which is applicable
to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model
269A, 269A-1, 269B, 269C, and TH-55A helicopters, was published in the
Federal Register on November 30, 1994 (59 FR 61298). That action
proposed to require a one-time radiographic inspection or other non-
destructive inspection of the applicable M/R drive shafts of all
affected Model 269 series helicopters. That action also proposed to
change paragraph (b) of AD 93-14-06 to exclude those replacement drive
shafts having an ``SZ'' or ``ZS'' prefix from mandatory inspections
prior to their installation.
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, except for editorial changes and
adding explanatory Note 1, relating to the scope of the applicability
statement when modifications, alterations, or repairs have been made in
the area subject to the requirements of the AD. The FAA has determined
that these changes will neither increase the economic burden on any
operator nor increase the scope of the AD.
The FAA estimates that 1,364 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 10 work hours per
helicopter to accomplish the required actions, and that the average
labor rate is $60 per work hour. Based on these figures, the total cost
impact of the AD on U.S. operators is estimated to be $818,400.
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.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-8630 (58 FR
53120, October 14, 1993), and by adding a new airworthiness directive
(AD), Amendment 39-9387, to read as follows:
AD 95-21-02 Schweizer Aircraft Corporation and Hughes Helicopters,
Inc: Amendment 39-9387. Docket No. 94-SW-02-AD. Supersedes AD 93-14-
06, Amendment 39-8630.
Applicability: Model 269A, 269A-1, 269B, 269C, and TH-55A
helicopters, with main rotor (M/R) drive shaft part number (P/N)
269A5305-3 or 269A5305-11 installed, except those M/R drive shafts
having a serial
[[Page 53266]]
number with a prefix of ``SZ'' or ``ZS'', certificated in any category.
Note 1: This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
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 use the authority
provided in paragraph (d) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent structural failure of the M/R drive shaft, separation
of the M/R from the helicopter, and subsequent loss of control of
the helicopter, accomplish the following:
(a) Inspect the M/R drive shaft for cracks, distortion,
corrosion, or other surface damage, using either the radiographic
inspection procedure or the other non-destructive inspection
procedure in accordance with Part I of Schweizer Service Bulletin B-
255.1 (SB), dated February 1, 1993. Conduct this inspection at the
time intervals and under the conditions stated in the following:
(1) Inspect M/R drive shafts with serial numbers (S/N) S0001
through S1111, and any drive shaft without an ``S'' prefix on the S/
N, having less than 1,100 hours time-in-service (TIS) on the
effective date of this AD--
(i) At the next removal of the drive shaft;
(ii) Within the next 600 hours TIS;
(iii) Prior to attaining 1,200 hours total TIS; or
(iv) Within 1 year after the effective date of this AD,
whichever occurs first.
(2) Inspect M/R drive shafts with S/N S0001 through S1111, and
any drive shaft without an ``S'' prefix on the S/N with 1,100 hours
or more TIS on the effective date of this AD--
(i) Within the next 100 hours TIS; or
(ii) At the next removal of the drive shaft; or
(iii) Within 1 year after the effective date of this AD,
whichever occurs first.
(3) Inspect M/R drive shafts with S/N S1112 and higher,
regardless of the number of the total hours TIS on the effective
date of this AD--
(i) Within the next 25 hours TIS;
(ii) At the next removal of the drive shaft; or
(iii) Within 1 year after the effective date of this AD,
whichever occurs first.
(4) Inspect the M/R drive shaft before further flight if M/R
vibrations occur that cannot be corrected with track and balance
procedures, or if M/R track and balance procedures are required more
than once within a 25-hour TIS interval.
(b) Inspect any replacement M/R drive shaft, except those that
have a serial number with a prefix of ``SZ'' or ``ZS'', prior to
installation in accordance with the procedures in Part I of the SB,
dated February 1, 1993.
(c) Replace any unairworthy M/R drive shaft with an airworthy M/
R drive shaft before further flight.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when approved by the Manager, New York Aircraft Certification
Office, FAA. 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) only for those helicopters that do not
exhibit M/R vibrations due to uncorrected out-of-track or out-of-
balance conditions specified in paragraph (a)(4) of this AD. The
special flight permit allows flight of the helicopter to a location
where the requirements of this AD can be accomplished.
(f) The inspections and replacement, if necessary, shall be done
in accordance with Schweizer Service Bulletin B-255.1 (SB), dated
February 1, 1993. This incorporation by reference was previously
approved by the Director of the Federal Register in accordance with
5 U.S.C. 552(a) and 1 CFR part 51 as of October 29, 1993 (58FR53120,
October 14, 1993). 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 Assistant Chief Counsel, 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.
(g) This amendment becomes effective on November 17, 1995.
Issued in Fort Worth, Texas, on September 28, 1995.
Daniel P. Salvano,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-25330 Filed 10-12-95; 8:45 am]
BILLING CODE 4910-13-U
