[Federal Register Volume 66, Number 209 (Monday, October 29, 2001)]
[Proposed Rules]
[Pages 54453-54463]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-26966]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 66, No. 209 / Monday, October 29, 2001 / 
Proposed Rules  

[[Page 54453]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-17-AD]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes superseding an existing airworthiness 
directive (AD) for Model OH-13E, OH-13H, and OH-13S helicopters 
manufactured by Bell Helicopter Textron, Inc. (BHTI). That AD currently 
requires either recurring liquid penetrant or eddy current inspections 
of the main rotor blade grip (grip) threads for a crack. If a crack is 
detected, that AD requires, before further flight, replacing the 
cracked grip with an airworthy grip. That AD also establishes a 
retirement life of 1200 hours time-in-service (TIS) for each grip. This 
proposed AD would add two part numbers (P/N) to the applicability and 
requires only recurring eddy current inspections of the grip threads. 
This proposed AD would also require reporting any results of the grip 
inspections to the FAA Rotorcraft Certification Office. This proposal 
is prompted by the issuance of an AD for the civil BHTI Model 47 
helicopters and the results of an accident investigation, an operator 
survey conducted by a trade association, various comments concerning 
the subject of the current AD, and a further analysis of field service 
data related to the BHTI Model 47 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: Comments must be received on or before December 28, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2001-SW-17-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m. Monday through Friday, except Federal holidays.

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:

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 will 
be considered before taking action on the proposed rule. The proposals 
contained in this document 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 mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2001-SW-17-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. 2001-SW-17-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137.

Discussion

    On May 12, 1987, the FAA issued AD 86-06-08R1, Amendment 39-5260 
(52 FR 24135, June 29, 1987) that amended AD 86-06-08, Amendment 39-
5626 (51 FR 11300, April 2, 1986) for BHTI Model 47 helicopters. Those 
ADs required certain fluorescent dye penetrant inspections of each 
grip. On August 31, 2000, the FAA issued Emergency AD 2000-18-51 for 
BHTI Model 47 helicopters that superseded AD 86-06-08 and the revision 
of that AD, 86-06-08R1. AD 2000-18-51 required certain liquid penetrant 
or eddy current inspections of the grip threads for a crack and, before 
further flight, replacing any cracked grip with an airworthy grip. That 
AD also established a retirement life of 1200 hours TIS for each grip. 
To address the same unsafe condition as addressed for the Model 47 
series helicopters, the FAA issued Emergency AD 2001-18-52 on September 
1, 2000, for Model OH-13E, OH-13H, and OH-13S helicopters manufactured 
by BHTI.
    Those actions were prompted by the results of an investigation of 
an August 1998 Canadian accident in which a grip failed on a BHTI Model 
47G-2 helicopter due to a fatigue crack. An analysis of field service 
data revealed fatigue cracks in the majority of the grips inspected. 
The requirements of AD 2000-18-52 are intended to prevent failure of a 
grip, loss of a main rotor blade, and subsequent loss of control of the 
helicopter.
    Since issuing AD 2000-18-52, other cracked grips with less than 
1200 hours TIS have been discovered, including one grip with a 2-inch 
crack through the grip. Since then, the FAA has determined that the 
liquid penetrant inspection is inadequate for finding smaller cracks in 
the grip threads. Additionally, two parts produced under a Parts 
Manufacturer Approval (PMA), P/Ns R74-120-252-11 and R74-120-135-5, 
were inadvertently omitted from the applicability of AD 2000-18-52. 
Based on these findings, an accident

[[Page 54454]]

investigation, a further analysis of field service data, and the 
results of an operator survey conducted by a trade association, the FAA 
is proposing to supersede AD 2000-18-52. Also, some of these proposals 
are based on the comments received in response to AD 2000-18-51 and 
addressed by the FAA in AD 2001-17-17, Amendment 39-12408 (66 FR 45584, 
August 29, 2001). Those comments pertain to the Model 47 series 
helicopters as well as the Model OH-13E, OH-13H, and OH-13S helicopters 
that have the same blade grips installed.
    We have identified an unsafe condition that is likely to exist or 
develop on Model OH-13E, OH-13H, and OH-13S helicopters. The proposed 
AD would supersede AD 2000-18-52 to require the following:
     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, and for grips manufactured 
under PMA, P/N 74-120-252-11, 74-120-135-5, R74-120-252-11, and R74-
120-135-5, conduct eddy current inspections of the threads of both 
grips as follows:
     Within 300 hours TIS since initial installation on any 
helicopter or within 10 hours TIS for grips with 300 or more hours TIS, 
or within 200 hours TIS since last liquid penetrant or eddy current 
inspection, whichever comes first, conduct an eddy current inspection 
in accordance with the procedures in Appendix 1 of this AD or an 
equivalent FAA-approved procedure that contains the requirements of the 
procedure in Appendix 1. Thereafter, conduct the eddy current 
inspection at intervals not to exceed 300 hours TIS.
     Report the results of each inspection to the FAA 
Rotorcraft Certification Office by providing the information requested 
in the sample format report in Appendix 3 of this AD. Reporting 
requirements have been approved by the Office of Management and Budget 
and assigned OMB control number 2120-0056.
     Before further flight, replace any cracked grip with an 
airworthy grip.
    The proposed AD would require maintaining the current retirement 
life of 1200 hours TIS for each affected grip.
    The FAA estimates that 300 helicopters of U.S. registry would be 
affected by this AD, that it would take approximately 10 work hours per 
helicopter to accomplish the disassembly, inspection, and reassembly of 
the grips from the helicopter, and that the average labor rate is $60 
per work hour. Required parts, if a grip needs to be replaced, would 
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.
    The regulations adopted herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    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 removing Amendment 39-11984 and by 
adding a new airworthiness directive to read as follows:

Continental Copters, Inc.; Gifton McCreay (Formerly Aerodyne Systems 
Engineering, Ltd., Formerly Texas Helicopter Corp.); Hawkeye Rotor 
and Wing Flight School; and Teryjon Aviation Inc.: Docket No. 2001-
SW-17-AD. Supersedes AD 2000-18-52, Amendment 39-11984, Docket No. 
2000-SW-36-AD.
    Applicability: Model OH-13E, OH-13H, and OH-13S helicopters 
manufactured by Bell Helicopter Textron, Inc. (BHTI), 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, 
74-120-135-5, R74-120-252-11, or R74-120-135-5, 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 (e) 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) Conduct an eddy current inspection of the threads of both 
grips for a crack in accordance with Appendix 1 of this AD or an 
equivalent FAA-approved procedure containing the requirements of the 
procedure in Appendix 1 within 300 hours time-in-service (TIS) since 
initial installation on any helicopter or within 10 hours TIS for 
grips with 300 or more hours TIS or within 200 hours TIS since the 
last liquid penetrant or eddy current inspection of grip threads, 
whichever comes first.
    (1) Thereafter, conduct the eddy current inspection in 
accordance with Appendix 1 of this AD or an equivalent FAA-approved 
procedure containing the requirements of the procedure in Appendix 1 
at intervals not to exceed 300 hours TIS.
    (2) Report the results of each inspection to the FAA Rotorcraft 
Certification Office within 7 calendar days. Reporting requirements 
have been approved by the Office of Management and Budget and 
assigned OMB control number 2120-0056.

    Note 2: See Appendix 2 of this AD for a list of known eddy 
current inspection facilities.

    (b) If a crack is detected, before further flight, replace any 
cracked grip with an airworthy grip.
    (c) On or before 1200 hours TIS, replace each grip with an 
airworthy grip.
    (d) This AD establishes a retirement life of 1200 hours TIS for 
the 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, 74-120-135-5, R74-
120-252-11, and R74-120-135-5.
    (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, 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.


[[Page 54455]]


    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Certification Office.

    (f) 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.

Appendix 1

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Appendix 2

Partial List of Nondestructive Inspection Testing Facilities Identified 
by Operators and FAA

Met Chem Testing Laboratories Inc., 369 W. Gregson Ave. (3085 S.), 
Salt Lake City, Utah 84115-3440, Phone: (801) 487-0801, Fax: (801) 
466-8790, www.metchemtesting.com.
Galactic NDT Services, 10728 D. South Pipeline RD, Hurst, Texas 
76053, Phone: (800) 458-6387.
Global Testing Technologies, 1173 North Service Rd. Unit D3, 
Oakville Toronto Canada, Phone: (905) 847-9300, Fax: (905) 847-9330.
Paragon Services, Inc., 1015 S. West St., Wichita, KS 67213, Phone: 
(316) 945-5285, Fax: (316) 945-0629.
NOE Services, 8775 E. Orchard Rd. #809, Englewood, CO, Phone: (303) 
741-0518, Fax: (303) 741-0519.
Applied Technical Services, Inc., 1190 Atlanta Industrial Drive, 
Marietta, GA 30066, Phone: (770) 423-1400, Fax: (770) 514-3299.
Rotorcraft Support, Van Nuys CA 91406, Phone: (818) 997-7667,
    Fax: (818) 997-1513.
Other FAA Approved repair facilities may be used.

Appendix 3

AD Compliance Inspection Report (Sample Format) Model OH-13 Main Rotor 
Blade Grip

Provide the following information and mail or fax it to: Manager, 
Rotorcraft Certification Office, Federal Aviation Administration, 
Fort Worth, Texas, 76193-0170, USA, Fax: 817-222-5783.
Aircraft Registration No:
Helicopter Model:
Helicopter Serial Number:
Owner and Operator of the Helicopter:

 
                                Grip #1                  Grip #2
 
Part Number:
Serial Number:
 

Hours TIS on the part at Inspection:
Crack Found (Y/N)
If yes, describe below.

Description of Findings

    Who performed the inspections?
    If a crack was found, describe the crack size, location, and 
orientation (provide a sketch or pictures with the grip part and 
serial number).
    Provide any other comments.

    Issued in Fort Worth, Texas, on October 11, 2001.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 01-26966 Filed 10-26-01; 8:45 am]
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