[Federal Register Volume 62, Number 97 (Tuesday, May 20, 1997)]
[Proposed Rules]
[Pages 27554-27556]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-13083]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-SW-28-AD]


Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 
47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 
47J, 47J-2, 47J-2A, and 47K 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 Bell Helicopter Textron, Inc. 
(BHTI) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-
3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 
47H-1, 47J, 47J-2, 47J-2A, and 47K helicopters. This proposal would 
require installing a safety washer kit designed to preclude separation 
of the stabilizer bar damper link (damper link) if the damper link rod 
end bushing (bushing) loosens and exits the damper link rod end. This 
proposal is prompted by two reported incidences in which the bushings 
loosened and exited the damper link rod ends, allowing the damper link 
to slide over the retention bolt and separate from the stabilizer bar 
(in the first incident), and from the hydraulic damper (in the second 
incident). The actions specified by the proposed AD are intended to 
prevent failure of the stabilizer bar damper link assembly, which can 
result in degraded control response and subsequent loss of control of 
the helicopter.

DATES: Comments must be received by July 21,1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 96-SW-28-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.
    The service information referenced in the proposed rule may be 
obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, 
Texas 76101. This information may be examined at the FAA, Office of the 
Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas.

FOR FURTHER INFORMATION CONTACT: Mr. Jurgen E. Priester, Aerospace 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5159, 
fax (817) 222-5960.

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 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

[[Page 27555]]

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. 96-SW-28-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 Assistant Chief Counsel, Attention: Rules 
Docket No. 96-SW-28-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

Discussion

    This document proposes the adoption of a new AD that is applicable 
to BHTI Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 
47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 
47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K helicopters. This proposal 
would require installing a safety washer kit designed to preclude 
separation of the damper link if the bushing loosens and exits the 
damper link rod end. This proposal is prompted by two reported 
incidences in which the bushings loosened and exited the damper link 
rod ends, allowing the damper link to slide over the retention bolt and 
separate from the stabilizer bar (in the first incident), and from the 
hydraulic damper (in the second incident). In the first incident, an 
inspection revealed that the rod end bearing had not been lubricated 
for an extended period of time prior to failure. In the second 
incident, a pilot safely landed the aircraft after reporting degraded 
control response. A post-flight inspection revealed that one damper 
link had separated from the hydraulic damper. A later inspection 
indicated that the bushing had not been properly roll-staked by the 
damper manufacturer. Therefore, one of the occurrences is attributed to 
a quality control problem with the damper link manufacturer. This 
condition, if not corrected, could result in failure of the stabilizer 
bar damper link assembly, which can result in degraded control response 
and subsequent loss of control of the helicopter.
    The FAA has reviewed BHTI Alert Service Bulletin (ASB) No. 47-96-
22, dated August 16, 1996, which describes procedures for removing and 
marking the stabilizer and damper link assemblies, installing a safety 
washer kit, part number (P/N) CA-047-96-022-1, applying a corrosion 
preventive compound, and reinstalling the stabilizer bar damper link 
assemblies. The ASB states that these actions are to be accomplished at 
the next 100-hour inspection, or no later than December 31, 1996. The 
FAA has determined that the compliance time should be within the next 
100 hours time-in-service (TIS) or no later than 120 calendar days 
after the effective date of the AD, whichever occurs first.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other BHTI Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-
2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-
4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K 
helicopters of the same type design, the proposed AD would require, 
within the next 100 hours TIS or within the next 120 calendar days 
after the effective date of the proposed AD, whichever occurs first, 
removing and marking the stabilizer and damper link assemblies, 
installing a safety washer kit, P/N CA-047-96-022-1, applying a 
corrosion preventive compound, and reinstalling the stabilizer and 
damper link assemblies. The actions would be required to be 
accomplished in accordance with the service bulletin described 
previously.
    The FAA estimates that 1,868 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take 1 work hour per 
helicopter to accomplish the proposed actions, and that the average 
labor rate is $60 per work hour. Required parts would cost 
approximately $188 per helicopter. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$463,264.
    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:

Bell Helicopter Textron, Inc.: Docket No. 96-SW-28-AD.

    Applicability: Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 
47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-
4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47K helicopters, 
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 (b) 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 within the next 100 hours time-in-service 
or within the next 120 calendar days after the effective date of 
this AD, whichever occurs first, unless accomplished previously.
    To prevent failure of the stabilizer bar damper link assembly, 
which can result in degraded control response and subsequent loss of 
control of the helicopter, accomplish the following:
    (a) Remove the stabilizer bar damper link assemblies from the 
helicopter, install a

[[Page 27556]]

safety washer kit, part number (P/N) CA-047-96-022-1, and reinstall 
the stabilizer bar damper link assemblies onto the helicopter in 
accordance with the Accomplishment Instructions contained in Bell 
Helicopter Textron, Inc. Alert Service Bulletin No. 47-96-22, dated 
August 16, 1996.
    (b) 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, Rotorcraft Certification Office, 
Rotorcraft Directorate, FAA. Operators shall submit their requests 
through an FAA Principal Maintenance Inspector, who may concur or 
comment and then send it to the Manager, Rotorcraft Certification 
Office.

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

    (c) 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.

    Issued in Fort Worth, Texas, on May 9, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-13083 Filed 5-19-97; 8:45 am]
BILLING CODE 4910-13-U