[Federal Register Volume 65, Number 221 (Wednesday, November 15, 2000)]
[Rules and Regulations]
[Pages 68873-68875]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-29050]



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Rules and Regulations
                                                Federal Register
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Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / 
Rules and Regulations

[[Page 68873]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-36-AD; Amendment 39-11984; AD 2000-18-52]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, Inc.--
Manufactured Model OH-13E, OH-13H, and OH-13S Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2000-18-52 which was sent 
previously to all known U.S. owners and operators of Bell Helicopter 
Textron, Inc. (BHTI)-manufactured Model OH-13E, OH-13H, and OH-13S 
helicopters by individual letters. This AD requires a liquid penetrant 
or eddy current inspection of the threads on each main rotor blade grip 
(grip) for a crack. The inspections must be accomplished within 100 
hours time-in-service (TIS) since initial installation on any 
helicopter or within 10 hours TIS for grips with 100 or more hours TIS 
and thereafter at intervals not to exceed 200 hours TIS. This AD also 
establishes a retirement life of 1200 hours TIS for affected grips. 
This amendment is prompted by the results of an investigation of an 
August 1998 accident in which a grip failed on a BHTI Model 47G-2 
helicopter due to a fatigue crack. The OH-13E, OH-13H, and OH-13S 
helicopters use the same grips as the Model 47G-2 helicopters. The 
actions specified by this AD are intended to prevent failure of a grip, 
loss of a main rotor blade, and subsequent loss of control of the 
helicopter.

DATES: Effective November 30, 2000, to all persons except those persons 
to whom it was made immediately effective by Emergency AD 2000-18-52, 
issued on September 1, 2000, which contained the requirements of this 
amendment.
    Comments for inclusion in the Rules Docket must be received on or 
before January 16, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2000-SW-36-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: <a href="/cdn-cgi/l/email-protection#241d09455753094540474b4949414a5057644245450a434b52"><span class="__cf_email__" data-cfemail="ab9286cad8dc86cacfc8c4c6c6cec5dfd8ebcdcaca85ccc4dd">[email protected]</span></a>.

FOR FURTHER INFORMATION CONTACT: Marc Belhumeur, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5177, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION: On May 12, 1987, the FAA issued AD 86-06-
08R1, Docket No. 86-ASW-10 (52 FR 24135, June 29, 1987), which amended 
AD 86-06-08 (51 FR 11300, April 2, 1986). Those AD's required an 
initial and repetitive fluorescent dye penetrant inspection of each 
grip on BHTI Model 47 helicopters and on BHTI-manufactured Model OH-
13E, OH-13H, and OH-13S helicopters. On August 31, 2000, the FAA issued 
AD 2000-58-51, Docket No. 2000-SW-35-AD, that superseded those previous 
AD's, changed the compliance time, and established a retirement life 
for the grips on the BHTI Model 47 series helicopters. To address the 
same unsafe condition as is addressed for the Model 47 series 
helicopters in AD 2000-58-51, the FAA issued Emergency AD 2000-18-52 on 
September 1, 2000 for BHTI-manufactured Model OH-13E, OH-13H, and OH-
13S helicopters. The emergency AD requires a liquid penetrant or eddy 
current inspection of the threads on each grip for a crack. The 
inspections must be accomplished within 100 hours TIS since initial 
installation on any helicopter or within 10 hours TIS for grips with 
100 or more hours TIS, and thereafter at intervals not to exceed 200 
hours TIS. That emergency AD also establishes a retirement life of 1200 
hours TIS for affected grips. That action was prompted by the results 
of an investigation of an August 1998 accident in which a grip failed 
on a BHTI Model 47G-2 helicopter due to a fatigue crack. An analysis of 
Australian field service data revealed fatigue cracks in the majority 
of the grips inspected. Since issuance of Emergency AD 2000-18-52, 
other cracked grips with less than 1200 hours TIS have been discovered. 
The OH-13E, OH-13H, and OH-13S helicopters use the same grips as the 
Model 47G-2 helicopters. This condition, if not corrected, could result 
in failure of a grip, loss of a main rotor blade, and subsequent loss 
of control of the helicopter.
    Since the unsafe condition described is likely to exist or develop 
on other BHTI-manufactured Model OH-13E, OH-13H, and OH-13S helicopters 
of the same type design, the FAA issued Emergency AD 2000-18-52 to 
prevent failure of a grip, loss of a main rotor blade, and subsequent 
loss of control of the helicopter. The AD requires the following:
    <bullet> Within the first 100 hours TIS since initial installation 
on any helicopter or within the next 10 hours TIS if 100 hours TIS has 
been exceeded, conduct a liquid penetrant or eddy current inspection of 
the grip threads for a crack.
    <bullet> Thereafter, conduct the liquid penetrant or eddy current 
inspection at intervals not to exceed 200 hours TIS.
    <bullet> If a crack is detected, before further flight, replace the 
cracked grip with an airworthy grip.
    <bullet> Establish a retirement life of 1200 hours TIS.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
structural integrity and controllability of the helicopter. Therefore, 
the above actions are required at the specified time intervals, and 
this AD must be issued immediately.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual letters 
issued on September 1, 2000 to

[[Page 68874]]

all known U.S. owners and operators of BHTI-manufactured Model OH-13E, 
OH-13H, and OH-13S helicopters. These conditions still exist, and the 
AD is hereby published in the Federal Register as an amendment to 
section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to 
make it effective to all persons.
    The FAA estimates that 300 helicopters of U.S. registry will be 
affected by this AD, that it will take approximately 10 work hours per 
helicopter to accomplish either inspection, and that the average labor 
rate is $60 per work hour. Required parts, if a grip needs to be 
replaced, will cost approximately $4,000 per grip (there are two grips 
on each helicopter). Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $2,580,000, assuming one 
inspection per helicopter and replacement of both grips on each 
helicopter.

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 mailed 
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. 2000-SW-36-AD.'' The postcard will be date 
stamped and returned to the commenter.
    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham 
Blvd., Room 663, Fort Worth, Texas.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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.


Sec. 39.13  [Amended]

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

2000-18-52  Gifton McCreay (Formerly Aerodyne Systems Engineering, 
LTD., Formerly Texas Helicopter Corp.), Continental Copters, Inc., 
Teryjon Aviation Inc., Hawkeye Rotor and Wing Flight School: 
Amendment 39-11984. Docket No. 2000-SW-36-AD.

    Applicability: Bell Helicopter Textron, Inc. (BHTI)-manufactured 
Model OH-13E, OH-13H, and OH-13S helicopters, with main rotor blade 
grips, part number (P/N) 47-120-135-2, 47-120-135-3, 47-120-135-5, 
47-120-252-1, 47-120-252-7, 47-120-252-11, 74-120-252-11, and 74-
120-135-5, 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 (c) 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 a main rotor blade grip (grip), separation 
of a main rotor blade, and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Within 100 hours time-in-service (TIS) since initial 
installation on any helicopter or within 10 hours TIS for grips with 
100 or more hours TIS, conduct a liquid penetrant or eddy current 
inspection of the grip threads for a crack. Thereafter, conduct the 
liquid penetrant or eddy current inspection at intervals not to 
exceed 200 hours TIS. If a crack is detected, before further flight, 
replace the cracked grip with an airworthy grip.
    (b) On or before 1200 hours TIS, replace each grip with an 
airworthy grip. This AD establishes a retirement life of 1200 hours 
TIS for grips, P/N 47-120-135-2, 47-120-135-3, 47-120-135-5, 47-120-
252-1, 47-120-252-7, 47-120-252-11, 74-120-252-11, and 74-120-135-5.
    (c) 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, 
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.

    (d) Special flight permits may be issued in accordance with 14 
CFR 21.197 and 21.199 to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (e) This amendment becomes effective on November 30, 2000, to 
all persons except those persons to whom it was made immediately 
effective by Emergency AD 2000-18-52, issued September 1, 2000, 
which contained the requirements of this amendment.


[[Page 68875]]


    Issued in Fort Worth, Texas, on November 2, 2000.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-29050 Filed 11-14-00; 8:45 am]
BILLING CODE 4910-13-U


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