[Federal Register Volume 65, Number 221 (Wednesday, November 15, 2000)]
[Rules and Regulations]
[Pages 68884-68885]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-29049]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-SW-35-AD; Amendment 39-11983; AD 2000-18-51]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G2A, 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: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting superseding Airworthiness Directive (AD) 2000-18-51 which was 
sent previously to all known U.S. owners and operators of Bell 
Helicopter Textron, Inc. (BHTI) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-
2, 47G2A, 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 by individual letters. This AD requires recurring liquid 
penetrant or eddy current inspections of the main rotor blade grip 
(grip) threads for a crack. If a crack is detected, this AD requires, 
before further flight, replacing the cracked grip with an airworthy 
grip. This AD also establishes a retirement life of 1,200 hours time-
in-service (TIS) for each grip. 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. An 
analysis of the field service data revealed fatigue cracks in 70 
percent of the grips inspected. 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 2000-18-51, 
issued on August 31, 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-35-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#41786c2032366c2025222e2c2c242f3532012720206f262e37"><span class="__cf_email__" data-cfemail="744d59150703591510171b1919111a0007341215155a131b02">[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: The FAA issued AD 86-06-08R1 on May 12, 1987 
(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 August 31, 2000, 
the FAA issued Emergency AD 2000-18-51, for BHTI Model 47B, 47B-3, 47D, 
47D-1, 47G, 47G-2, 47G2A, 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. That emergency AD supersedes AD 86-06-08 and AD 86-06-
08R1 and requires recurring liquid penetrant or eddy current 
inspections of the grip threads for a crack. If a crack is detected, 
the AD requires, before further flight, replacing the cracked grip with 
an airworthy grip. The AD also establishes a retirement life of 1,200 
hours TIS for each grip. 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 2000-18-51, 
other cracked grips with less than 1200 hours TIS have been discovered. 
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 Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G2A, 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 
designs, the FAA issued Emergency AD 2000-18-51 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 for 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, 
and 47-120-252-11, and for grips manufactured under Parts Manufacturer 
Approval, P/N 74-120-252-11 and 74-120-135-5:
    <bullet> Within 100 hours 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.
    <bullet> Thereafter, conduct the liquid penetrant or eddy current 
inspection of the grip threads 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 time-in-service 
(TIS) for each grip.
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 2000-18-51 to all known U.S. owners and operators of BHTI 
Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G2A, 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. 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 1000 helicopters of U.S. registry will be

[[Page 68885]]

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 $8,600,000, 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-35-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 
location provided under the caption ADDRESSES.

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 removing Amendment 39-5260 (51 FR 
11300, April 2, 1986) and Amendment 39-5626 (52 FR 24135, June 29, 
1987) and by adding a new airworthiness directive to read as follows:

2000-18-51  Bell Helicopter Textron, Inc.: Amendment 39-11983. 
Docket No. 2000-SW-35-AD. Supersedes AD 86-06-08, Amendment 39-5260, 
and AD 86-06-08 R1, Amendment 39-5626, Docket No. 86-ASW-10.

    Applicability: Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G2A, 
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, 
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 2000-18-51, issued August 31, 2000, which 
contained the requirements of this amendment.

    Issued in Fort Worth, Texas, on November 2, 2000.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 00-29049 Filed 11-14-00; 8:45 am]
BILLING CODE 4910-13-U


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