[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]


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

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).

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

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