[Federal Register Volume 63, Number 217 (Tuesday, November 10, 1998)]
[Proposed Rules]
[Pages 62973-62975]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-30047]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-39-AD]
Airworthiness Directives; Schweizer Aircraft Corporation and
Hughes Helicopters, Inc. Model 269C-1 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to Schweizer Aircraft Corporation and
Hughes Helicopters, Inc. (Schweizer) Model 269C-1 helicopters. This
proposal would require a visual inspection of the bond line between the
main rotor blade (blade) abrasion strip (abrasion strip) and the blade
for voids, separation, or lifting of the abrasion strip; a visual
inspection of the adhesive bead around the perimeter of the abrasion
strip for erosion, cracks, or blisters; a tap (ring) test of the
abrasion strip for debonding or hidden corrosion voids; and removal of
any blade with an unairworthy abrasion strip and replacement with an
airworthy blade. This proposal is prompted by four reports that
indicate that debonding and corrosion have occurred on certain blades
where the abrasion strip attaches to the blade skin. The actions
specified by the proposed AD are intended to prevent loss of the
abrasion strip from the blade and subsequent loss of control of the
helicopter.
DATES: Comments must be received on or before January 11, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-39-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. Comments may be inspected at this location
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal
holidays.
FOR FURTHER INFORMATION CONTACT: Raymond Reinhardt, Aerospace Engineer,
FAA, New York Aircraft Certification Office, Airframe and Propulsion
Branch, Engine and Propeller Directorate, 10 Fifth Street, 3rd Floor,
Valley Stream, New York 11581-1200, telephone (516) 256-7532, fax (516)
568-2716.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The
[[Page 62974]]
proposals contained in this notice may be changed in light of the
comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 98-SW-39-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-39-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
Discussion
This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to Schweizer Model 269C-1
helicopters. This proposal would require a visual inspection of the
bond line between the blade abrasion strip and the blade for voids,
separation, or lifting of the abrasion strip; a visual inspection of
the adhesive bead around the perimeter of the abrasion strip for
erosion, cracks, or blisters; a tap (ring) test of the abrasion strip
for debonding or hidden corrosion voids; and removal of any blade with
an unairworthy abrasion strip and replacement with an airworthy blade.
This proposal is prompted by four reports that indicate that debonding
and corrosion have occurred on certain blades where the abrasion strip
attaches to the blade skin. This condition, if not corrected, could
result in loss of the abrasion strip from the blade and subsequent loss
of control of the helicopter.
Since an unsafe condition has been identified that is likely to
exist or develop on other Schweizer Model 269C-1 helicopters of the
same type design, the proposed AD would require a visual inspection of
the bond line between the main rotor blade abrasion strip and the blade
for voids, separation, or lifting of the abrasion strip; a visual
inspection of the adhesive bead around the perimeter of the abrasion
strip for erosion, cracks, or blisters; a tap (ring) test of the
abrasion strip for debonding or hidden corrosion voids; and removal of
any blade with an unairworthy abrasion strip and replacement with an
airworthy blade. Repair of an affected blade's abrasion strip is
considered a terminating action for the requirements of this AD.
The FAA estimates that 47 helicopters of U.S. registry would be
affected by this proposed AD, that it would take approximately one-
third of a work hour per helicopter to conduct the initial inspections;
approximately one-third of a work hour to conduct the repetitive
inspections; approximately 11 work hours to remove and reinstall a
blade; and approximately 32 work hours to repair the blade; and that
the average labor rate is $60 per work hour. Required parts
(replacement abrasion strips) would cost approximately $57 per main
rotor abrasion strip (each helicopter has three main rotor blades).
Based on these figures, the total cost impact of the AD on U.S.
operators is estimated to be $65,168 per year for the first year and
approximately $64,228 for each of the next 5 years thereafter, assuming
24 of the affected blades (approximately 1/6 of the fleet or the blades
on 8 helicopters) in the fleet are removed, repaired, and reinstalled
with replacement abrasion strips each year, and that all affected
helicopters are subjected to one repetitive inspection each year,
including the first year.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Schweizer Aircraft Corporation and Hughes Helicopters, Inc.: Docket
No. 98-SW-39-AD.
Applicability: Model 269C-1 helicopters with main rotor blades,
P/N 269A1185-1, S/N S222, S312, S313, S325, S326, S327, S339, S341,
S343, S346, S347, S349 through S367, S369 through S377, S379 through
S391, S393, S394, S395, S397, S399, S401 through S417, S419 through
S424, S426 through S449, S451 through S507, S509 through S513, S516
through S527, S529 through S540, S542, S544 through S560, S562
through S584, S586 through S595, S597 through S611, S620 through
S623, S625, S628, S633, S641 through S644, S646, S653, S658, S664,
S665, and S667, 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
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 (e) 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 loss of the abrasion strip from a main rotor blade
(blade) and subsequent loss of control of the helicopter, accomplish
the following:
(a) Within the next 50 hours time-in-service (TIS), or within 90
calendar days after the effective date of this AD, whichever is
earlier, or prior to installing an affected replacement blade, and
thereafter at intervals
[[Page 62975]]
not to exceed 50 hours TIS from the date of the last inspection or
replacement installation:
(1) Visually inspect the adhesive bead around the perimeter of
each abrasion strip for erosion, cracks, or blisters.
(2) Visually inspect the bond line between each abrasion strip
and each blade skin for voids, separation, or lifting of the
abrasion strip.
(3) Inspect each abrasion strip for debonding or hidden
corrosion voids using a tap (ring) test as described in the
applicable maintenance manual.
(b) If any deterioration of an abrasion strip adhesive bead is
discovered, prior to further flight, restore the bead in accordance
with the applicable maintenance manual.
(c) If abrasion strip debonding, separation, or a hidden
corrosion void is found or suspected, prior to further flight,
remove the blade with the defective abrasion strip and replace it
with an airworthy blade.
(d) Repair of an affected blade's abrasion strip is considered a
terminating action for the requirements of this AD. Identify the
repaired blade with a white dot added adjacent to the blade S/N.
(e) 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, 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.
(f) 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, provided the
abrasion strip has not started to separate or debond from the main
rotor blade.
Issued in Fort Worth, Texas, on November 3, 1998.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-30047 Filed 11-9-98; 8:45 am]
BILLING CODE 4910-13-U
