[Federal Register Volume 64, Number 152 (Monday, August 9, 1999)]
[Rules and Regulations]
[Pages 43058-43060]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-20057]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-52-AD; Amendment 39-11244; AD 99-16-09]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Model
230 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Bell Helicopter Textron Canada (BHTC) Model 230
helicopters. This action requires verifying the torque on the vertical
fin attachment bolts (bolts); 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 loss of control of the
helicopter.
DATES: Effective August 24, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 24, 1999.
Comments for inclusion in the Rules Docket must be received on or
before October 8, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-52-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
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: Harry Edmiston, Aerospace Engineer,
Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5158, fax
(817) 222-5783.
SUPPLEMENTARY INFORMATION: Transport Canada, which is the airworthiness
authority for Canada, recently notified the FAA that an unsafe
condition may exist on BHTC Model 230 helicopters. Transport Canada
advises that, in one instance, loss of torque on the bolts resulted in
the fracture of four of the eight bolts and a loose vertical fin on a
Model 230 helicopter.
BHTC has issued Bell Helicopter Textron Alert Service Bulletin No.
230-98-14, Revision A, dated June 9, 1998 (ASB), which specifies a bolt
torque check within 25 hours after receipt of the ASB; removal,
inspection, 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 No. 230-98-23, Revision A, dated July 1,
1998, which specifies a modification of the vertical fin attachment
fitting and tail boom fitting to permit installation of increased
diameter fin attachment hardware. Transport Canada classified these
service bulletins as mandatory and issued AD CF-98-22, dated August 7,
1998, in order to assure the continued airworthiness of these
helicopters in Canada.
This helicopter model is manufactured in Canada and is 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 the 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
[[Page 43059]]
develop on other BHTC Model 230 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 torque on
the bolts; inspecting the vertical fin and tail boom 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 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 17 helicopters will be affected by this AD,
that it will take approximately 8 work hours to accomplish the initial
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 $9,180, 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-52-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
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 99-16-09 Bell Helicopter Textron Canada: Amendment 39-11244.
Docket No. 98-SW-52-AD.
Applicability: Model 230 helicopters, serial numbers 23001
through 23038, 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 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 of Bell Helicopter Textron Alert Service Bulletin No.
230-98-14, Revision A, dated June 9, 1998 (ASB).
(b) On or before the next 150 hour TIS inspection, inspect the
vertical fin fitting and tail boom fitting for cracks, elongated
bolt holes, distortion, and corrosion in accordance with Part II of
the Accomplishment Instructions in the ASB. If elongation of a bolt
hole is detected, incorporate the modifications specified in Bell
Helicopter Textron Technical Bulletin No. 230-98-23, Revision A,
dated July 1, 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 the ASB.
[[Page 43060]]
(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 scheduled inspections, Part III, of the
Accomplishment Instructions in the ASB.
(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,
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.
(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. 230-98-14, Revision A,
dated June 9, 1998 and Bell Helicopter Textron Technical Bulletin
No. 230-98-23, Revision A, dated July 1, 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 August 24, 1999.
Note 3: The subject of this AD is addressed in Transport Canada
(Canada) AD CF-98-22, dated August 7, 1998.
Issued in Fort Worth, Texas, on July 28, 1999.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-20057 Filed 8-6-99; 8:45 am]
BILLING CODE 4910-13-U