[Federal Register: November 8, 2002 (Volume 67, Number 217)]
[Rules and Regulations]
[Page 68026-68027]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08no02-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-SW-42-AD; Amendment 39-12941; AD 2002-22-14]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. Model
204B, 205A, 205A-1, 205B, 212, 214B, and 214B-1 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD) for specified Bell Helicopter Textron, Inc. (BHTI) model
helicopters that requires reducing the retirement time for certain main
rotor tension-torsion (TT) straps on those models and on the Model UH-1
series helicopters. This document contains the same requirements as the
existing AD but removes the Model UH-1 series restricted category
helicopters and adds the BHTI Model 205A and 205B helicopters to the
applicability. This amendment is prompted by the issuance of a separate
AD for the Model UH-1 series helicopters and the need to add the BHTI
Model 205A and 205B helicopters to the applicability because the
affected straps are eligible for installation on these model
helicopters. The actions specified by this AD are intended to prevent
failure of a TT strap, loss of a main rotor blade, and subsequent loss
of control of the helicopter.
DATES: Effective December 13, 2002.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
5783.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for specified model helicopters was published in the
Federal Register on May 21, 2002 (67 FR 35763). On July 31, 1980, the
FAA issued AD 80-17-09, Amendment 39-3876 (45 FR 54014, August 14,
1980), Docket No. 80-ASW-25. That AD requires replacing certain TT
straps on or before attaining 1200 hours time in service (TIS) or 24
months, whichever occurs first, for the BHTI Model 204B, 205A-1, 212,
214B, 214B-1, and the Model UH-1 series military helicopters. That
action was prompted by an offshore accident of a BHTI Model 212
helicopter in which a TT strap reportedly failed in flight after 2,140
hours TIS with resulting loss of the main rotor blade. The requirements
of that AD are intended to prevent failure of a TT strap, loss of a
main rotor blade, and subsequent loss of control of the helicopter.
Since the issuance of that AD, a separate AD was issued (67 FR
61771, October 2, 2002) for the military surplus restricted category
helicopters that includes the Model UH-1 series helicopters, hence the
removal of the Model UH-1 series helicopters from the applicability of
this AD. Also, further review indicates that the affected TT straps are
eligible for installation on the BHTI Model 205A and 205B helicopters.
Therefore, this AD includes those models in the applicability.
To further address this unsafe condition that is likely to exist or
develop on other helicopters of these same type designs, this AD
supersedes AD 80-17-09. This AD contains the requirements of AD 80-17-
09 but changes the applicability by removing the restricted category
Model UH-1 series helicopters and adding the BHTI Model 205A and 205B
helicopters.
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 except for minor editorial changes.
These changes will neither increase the economic burden on operators
nor increase the scope of the AD.
The FAA estimates that this AD will affect 168 helicopters of U.S.
registry. The FAA also estimates that it will take 8 work hours to
replace the TT straps at an average labor rate of $60 per work hour.
The TT straps will cost approximately $10,484 per helicopter. Based on
these figures, the total cost
[[Page 68027]]
impact of the AD on U.S. operators is estimated to be $1,840,352.
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 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 39-3876 (45 FR
54014, August 14, 1980) and by adding a new airworthiness directive
(AD), Amendment 39-12941, to read as follows:
2002-22-14 Bell Helicopter Textron, Inc.: Amendment 39-12941. Docket
No. 2001-SW-42-AD. Supersedes AD 80-17-09, Amendment 39-3876, Docket
No. 80-ASW-25.
Applicability: Model 204B, 205A, 205A-1, 205B, 212, 214B, and
214B-1 helicopters, with main rotor tension-torsion (TT) strap, part
number (P/N) 204-012-122-1, -5, or 214-010-179-1, 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 (d) 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 separation of a TT strap, loss of a main rotor blade,
and subsequent loss of control of the helicopter, accomplish the
following:
(a) Before further flight, remove and replace any TT strap with
1,200 or more hours time-in-service (TIS) or 24 or more months since
initial installation on any helicopter, whichever occurs first.
(b) This AD revises the Limitations section of the maintenance
manual by establishing a life limit for the TT straps, P/N 204-012-
122-1, -5, or 214-010-179-1, of 1200 hours TIS or 24 months since
initial installation on any helicopter, whichever occurs first.
(c) Special flight permits will not be issued.
(d) 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.
(e) This amendment becomes effective on December 13, 2002.
Issued in Fort Worth, Texas, on October 28, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-28411 Filed 11-7-02; 8:45 am]
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