[Federal Register Volume 67, Number 34 (Wednesday, February 20, 2002)]
[Rules and Regulations]
[Pages 7594-7604]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3851]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-17-AD; Amendment 39-12657; AD 2002-03-16]
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.

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SUMMARY: This amendment supersedes 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 amendment adds two 
part numbers (P/N) to the applicability and requires only recurring 
eddy current inspections of the grip threads. This AD also requires 
reporting any results of the grip inspections to the FAA Rotorcraft 
Certification Office. This amendment 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.

EFFECTIVE DATE: March 27, 2002.

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.

[[Page 7595]]


SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by 
superseding AD 2000-18-52, Amendment 39-11984 (65 FR 68873, November 
15, 2000), which applies to BHTI-manufactured Model OH-13E, OH-13H, and 
OH-13S helicopters, was published in the Federal Register on October 
29, 2001 (66 FR 54453). That action proposed to supersede AD 2000-18-52 
and 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 Parts Manufacturer Approval, 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. Information 
collection requirements contained in this AD have been approved by the 
Office of Management and Budget (OMB) under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.
     Before further flight, replace any cracked grip with an 
airworthy grip. Also, the AD proposed maintaining the current 
retirement life of 1200 hours TIS for each affected grip.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed. However, a non-substantive change has 
been made to paragraph (a)(2) of the AD that describes the OMB 
information collection requirements; this change will neither increase 
the economic burden on any operator nor increase the scope of the AD.
    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 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, will 
cost approximately $4,000 per grip. There are two grips on each 
helicopter. Based on these figures, the total cost impact of this 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 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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 removing Amendment 39-11984 (65 FR 
68873, November 15, 2000), and by adding a new airworthiness directive 
(AD), Amendment 39-12657, to read as follows:

2002-03-16 Continental Copters, Inc.; Gifton McCreay (Formerly 
Aerodyne Systems Engineering, Ltd., Formerly Texas Helicopter 
Corp.); Hawkeye Rotor and Wing Flight School; and Teryjon Aviation 
Inc.: Amendment 39-12657. 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. Information collection 
requirements contained in this AD have been approved by the Office 
of Management and Budget (OMB) under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.

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


[[Page 7596]]


    (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.

    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.
    (g) This amendment becomes effective on March 27, 2002.

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.

[[Page 7604]]

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 February 6, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-3851 Filed 2-19-02; 8:45 am]
BILLING CODE 4910-13-U