AD 96-18-05 R1

AD Final Rules - 96-18-05 R1.pdf
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AD Number:
96-18-05 R1
Document Type:
AD Final Rules
Docket Number:
FAA-2008-1242
Subject Heading:
Airworthiness Directives; Bell Helicopter Textron Canada Model 206L, 206L-1, and 206L-3 Helicopters
Subject:
Tailboom
Status:
Current
Citation:
Federal Register: November 16, 2010 (Volume 75, Number 220)
Citation Publish Date:
11/16/2010
Effective Date:
12/21/2010
Make:
Bell Helicopter Textron Canada Limited
Model:
206L | 206L-1 | 206L-3
Product Type:
Aircraft
Product Subtype:
Rotorcraft
Affected AD:
Superseded AD:
96-18-05
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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[Federal Register: November 16, 2010 (Volume 75, Number 220)]


[Rules and Regulations]


[Page 69860-69861]


From the Federal Register Online via GPO Access [wais.access.gpo.gov]


[DOCID:fr16no10-4]


––––––––––––––––––––––––––––––––––


DEPARTMENT OF TRANSPORTATION


Federal Aviation Administration


14 CFR Part 39


[Docket No. FAA-2008-1242; Directorate Identifier 96-SW-13-AD; Amendment 39-16511; AD


96-18-05 R1]


RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 206L, 206L-1, and 206L-3


Helicopters


AGENCY:
 
Federal Aviation Administration, DOT.


ACTION:
 
Final rule.


––––––––––––––––––––––––––––––––––


SUMMARY:
 
This amendment revises an existing airworthiness directive (AD) for Bell Helicopter


Textron Canada (BHTC) Model 206L, 206L-1, and 206L-3 helicopters with a certain part numbered


tailboom installed, that currently requires a visual inspection of the tailboom skin in the areas around


the nutplates and in the areas of the tailboom drive shaft cover retention clips for cracks and corrosion


using a 10-power or higher magnifying glass until the tailboom is replaced with an airworthy


tailboom. This action requires the same actions as the existing AD, but allows a longer interval for


the repetitive inspections if the tailboom is modified to increase its structural integrity. Replacement


with an airworthy tailboom other than a part-numbered tailboom affected by this amendment


constitutes a terminating action for the requirements of this AD. This amendment is prompted by an


accident and several reports of fatigue cracks in the tailboom skin in the areas around the nutplates


for the tail rotor fairing and in the areas of the tail rotor drive shaft cover retention clips. The actions


required by this AD are intended to prevent failure of the tailboom and subsequent loss of control of


the helicopter.


DATES:
 
Effective December 21, 2010.


As of September 16, 1996 (61 FR 45876, August 30, 1996), the Director of the Federal Register


approved the incorporation by reference of Bell Helicopter Textron Inc. Alert Service Bulletin 206L-


87-47, Revision C, dated October 23, 1989, listed in this AD.


ADDRESSES:
 
You may get the service information identified in this AD from Bell Helicopter


Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or


(800) 363-8023, fax (450) 433-0272, or at http://www.bellcustomer.com/files/.


1
2


Examining the Docket: You may examine the docket that contains this AD, any comments, and


other information on the Internet at http://www.regulations.gov, or at the Docket Operations office,


West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.


FOR FURTHER INFORMATION CONTACT:
 
DOT/FAA Southwest Region, Sharon Miles,


ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Policy Group, 2601


Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5122, fax (817) 222-5961.


SUPPLEMENTARY INFORMATION:
 
A proposal to amend 14 CFR part 39 by revising AD 96-


18-05, Amendment 39-9729 (61 FR 45876, August 30, 1996), for the specified BHTC Model 206L,


206L-1, and 206L-3 helicopters, with tailboom, part number (P/N) 206-033-004-003, -011, -045, or -


103, installed, was published in the Federal Register on November 26, 2008 (73 FR 71955). The


action proposed to require before further flight, unless accomplished previously, a visual inspection


of the tailboom skin for cracks and corrosion in the areas around the nutplates for the tail rotor fairing


and in the areas of the tailboom drive shaft cover retention clips using a 10-power or higher


magnifying glass. The action also proposed to require the inspections repetitively at intervals not to


exceed 100 hours time-in-service (TIS) for helicopters that have been modified to increase the


structural integrity of the tailboom in accordance with Bell Helicopter Textron Alert Service Bulletin


No. 206L-87-47, Revision C, dated October 23, 1989 (ASB). For helicopters that have not been


modified in accordance with the ASB, we proposed to require repetitive inspections at intervals not to


exceed 50-hours TIS. That action also proposed a terminating action for the repetitive inspection


requirements by replacing an affected tailboom with an airworthy tailboom, P/N 206-033-004-143 or


-177. That action was prompted by an accident and several reports of fatigue cracks in the tailboom


skin in the areas around the nutplates for the tail rotor fairing, and in the areas of the tail rotor drive


shaft cover retention clips.


Transport Canada, the airworthiness authority for Canada, notified the FAA that an unsafe


condition may exist on BHTC Model 206L, 206L-1, and 206L-3 helicopters. Transport Canada


advises that there has been one accident and several reports of fatigue cracks in the tailboom skin in


the areas around the nutplates for the tail rotor fairing, and in the areas of the tail rotor drive shaft


cover retention clips.


This helicopter model is manufactured in Canada and is type certificated for operation in the


United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. When AD


96-18-05 was issued, the type certificate for these affected model helicopters was in the U.S. and the


FAA had oversight responsibility for these model helicopters. Transport Canada issued an AD


following the FAA AD, except that Transport Canada required modifying the tailboom in accordance


with the ASB and increasing the inspection interval to 100 hours TIS. Subsequently, these type


certificates were transferred to Canada.


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 with only minor, non-substantive changes.


We estimate that this AD will affect 551 helicopters of U.S. registry. We also estimate that it will


take about 0.8 work hour to inspect and 8 work hours per helicopter to modify a helicopter, at an


average labor rate of $85 per work hour. If a helicopter is modified to increase the inspection


intervals, required parts will cost approximately $385. Based on these figures, we estimate the total


cost impact of the AD on U.S. operators to be $423,168 per year, assuming all the helicopters are


unmodified and twelve 50-hour TIS inspections per helicopter. If we assume that all helicopters are


modified at the beginning of the year, the cost impact of the AD on U.S. operators will be $776,359


for the first year, assuming there are six 100-hour TIS inspections the first year, and $211,584 for


each year thereafter.