AD Amdt-39-11400

[Federal Register Volume 64, Number 213 (Thursday, November 4, 1999)]
[Rules and Regulations]
[Pages 60100-60102]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-28653]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-SW-51-AD; Amendment 39-11400; AD 99-23-04]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada Model 
222, 222B, and 222U Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 
and 222U helicopters. This action requires verifying the torque on each 
vertical fin attachment bolt (bolt); inspecting the vertical fin and 
tailboom fittings for cracks, elongation of bolt holes, distortion and 
corrosion; and re-verifying the torque on the bolts after inspecting 
the fittings. This amendment is prompted by a report of a loose 
vertical fin, which was discovered during a post-flight inspection. The 
actions specified in this AD are intended to prevent loss of torque of 
the bolts, which could lead to fracture of the bolts, separation of the 
vertical fin from the helicopter, and subsequent loss of control of the 
helicopter.

DATES: Effective November 19, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 19, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before January 3, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 98-SW-51-AD, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137.

[[Page 60101]]

    The service information referenced in this AD may be obtained from 
Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
JON1LO, telephone (800) 463-3036, fax (514) 433-0272. This information 
may be examined at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aerospace Engineer, 
Rotorcraft Standards Staff, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5122, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: Transport Canada, which is the airworthiness 
authority for Canada, has notified the FAA that an unsafe condition may 
exist on BHTC Model 222, 222B, and 222U helicopters. Transport Canada 
advises that, in one instance, loss of torque on the bolts resulted in 
fracture of four of the eight bolts and a loose vertical fin on a Model 
230 helicopter, which is of similar design to the Model 222 series 
helicopters.
    BHTC has issued Bell Helicopter Textron Alert Service Bulletin 
(ASB) No. 222-98-82, Revision A, and ASB No. 222U-98-53, Revision A, 
both dated June 9, 1998, which specify a bolt torque check within 25 
hours after receipt of the ASB; removal, inspection and modification, 
if necessary, and installation of the vertical fin at the next 
scheduled 150-hour inspection after receipt of the ASB; and verifying 
the bolt torque within 5 to 10 hours after each fin removal and 
installation, and at every 150 hours of operation. BHTC also issued 
Bell Helicopter Textron Technical Bulletin (TB) No. 222-98-156 
(applicable to Model 222 and 222B helicopters) and TB No. 222U-98-84 
(applicable to Model 222U helicopters), both dated June 17, 1998, which 
specify a modification of the vertical fin attachment fitting and 
tailboom fitting to permit installation of increased diameter fin 
attachment hardware. Transport Canada classified these service 
bulletins as mandatory and issued AD CF-98-21, dated August 7, 1998, in 
order to assure the continued airworthiness of these helicopters in 
Canada.
    These helicopter models are manufactured in Canada and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, Transport Canada has kept the FAA 
informed of the situation described above. The FAA has examined the 
findings of Transport Canada, reviewed all available information, and 
determined that AD action is necessary for products of this type design 
that are certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other BHTC Model 222, 222B, and 222U helicopters of 
the same type design registered in the United States, this AD is being 
issued to prevent loss of torque of the bolts, which could lead to 
fracture of the bolts, separation of the vertical fin from the 
helicopter, and subsequent loss of control of the helicopter. This AD 
requires verifying the bolt torque; inspecting the vertical fin and 
tailboom fittings for cracks, elongation of bolt holes, distortion and 
corrosion; and re-verifying the torque on the bolts after inspecting 
the fittings. The bolt torque must also be verified at specified 
intervals after accomplishing the initial inspections. The actions are 
required to be accomplished in accordance with the service bulletins 
described previously. The short compliance time involved is required 
because the previously described critical unsafe condition can 
adversely affect the structural integrity of the helicopter. Therefore, 
verifying the torque is required within 25 hours time-in-service, and 
this AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Cost Impact

    The FAA estimates that 78 helicopters will be affected by this AD, 
that it will take approximately 8 work hours to accomplish the torque 
verifications and vertical fin inspection, 1 work hour to accomplish 
repetitive torque verification and that the average labor rate is $60 
per work hour. Based on these figures, the total cost impact of the AD 
on U.S. operators for the initial inspection and 1 recurring inspection 
is estimated to be $42,120, assuming no helicopters require 
modification due to elongated bolt holes.

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 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. 98-SW-51-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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

[[Page 60102]]

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, Incorporation by 
reference, 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 adding a new airworthiness directive 
to read as follows:

AD 99-23-04  Bell Helicopter Textron Canada: Amendment 39-11400. 
Docket No. 98-SW-51-AD.

    Applicability: Model 222 helicopters, serial numbers (S/N) 47006 
through 47089; Model 222B helicopters, S/N 47131 through 47156, and 
Model 222U helicopters, S/N 47501 through 47574, certificated in any 
category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
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 loss of torque of the vertical fin attachment bolts 
(bolts), which could lead to fracture of the bolts, separation of 
the vertical fin from the helicopter, and subsequent loss of control 
of the helicopter accomplish the following:
    (a) Within 25 hours time-in-service (TIS), verify the torque on 
the bolts in accordance with Part I of the Accomplishment 
Instructions in Bell Helicopter Textron Alert Service Bulletin (ASB) 
No. 222-98-82, Revision A (applicable to Model 222 and Model 222B 
helicopters), or ASB No. 222U-98-53, Revision A (applicable to Model 
222U helicopters), both dated June 9, 1998.
    (b) On or before the next 150 hour TIS inspection, inspect the 
vertical fin fitting and tailboom fitting for cracks, elongated bolt 
holes, distortion and corrosion in accordance with Part II of the 
Accomplishment Instructions in ASB No. 222-98-82, Revision A 
(applicable to Model 222 and Model 222B helicopters), or ASB No. 
222U-98-53, Revision A, (applicable to Model 222U helicopters), both 
dated June 9, 1998. If bolt holes are elongated, modify the vertical 
fin fitting and tailboom fitting in accordance with the 
Accomplishment Instructions in Bell Helicopter Textron Technical 
Bulletin (TB) No. 222-98-156 (applicable to Model 222 and 222B 
helicopters), or TB No. 222U-98-84 (applicable to Model 222U 
helicopters), both dated June 17, 1998.
    (c) After the inspection required by paragraph (b) and after at 
least 5 hours TIS but within 10 hours TIS, re-verify the torque on 
the bolts in accordance with Part III, Special Inspections, Step 1 
of the Accomplishment Instructions in ASB No. 222-98-82, Revision A 
(applicable to Model 222 and Model 222B helicopters), or ASB No. 
222U-98-53, Revision A, (applicable to Model 222U helicopters), both 
dated June 9, 1998.
    (d) Thereafter, at intervals not to exceed 150 hours TIS, verify 
the torque of the vertical fin attachment bolts in accordance with 
the 150 flight hour, Part III, Scheduled Inspections of the 
Accomplishment Instructions in the ASB No. 222-98-82, Revision A 
(applicable to Model 222 and Model 222B helicopters), or ASB No. 
222U-98-53, Revision A, (applicable to Model 222U helicopters), both 
dated June 9, 1998.
    (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 Standards Staff, 
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 Standards Staff.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Rotorcraft Standards Staff.

    (f) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the helicopter to a location where 
the requirements of this AD can be accomplished.
    (g) The inspections shall be done in accordance with Bell 
Helicopter Textron Alert Service Bulletin No. 222-98-82, Revision A 
(applicable to Model 222 and Model 222B helicopters), or Bell 
Helicopter Textron Alert Service Bulletin 222U-98-53, Revision A 
(applicable to Model 222U helicopters), both dated June 9, 1998; and 
Bell Helicopter Textron Technical Bulletin No. 222-98-156 
(applicable to Model 222 and 222B helicopters), or Bell Helicopter 
Textron Technical Bulletin No. 222U-98-84 (applicable to Model 222U 
helicopters), both dated June 17, 1998. These incorporations by 
reference were approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Bell Helicopter Textron Canada, 12,800 Rue de 
l'Avenir, Mirabel, Quebec JON1LO, telephone (800) 463-3036, fax 
(514) 433-0272. Copies may be inspected at the FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.
    (h) This amendment becomes effective on November 19, 1999.

    Note 3: The subject of this AD is addressed in Transport Canada 
(Canada) AD CF-98-21, dated August 7, 1998.

    Issued in Fort Worth, Texas, on October 26, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-28653 Filed 11-3-99; 8:45 am]
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