[Federal Register Volume 64, Number 11 (Tuesday, January 19, 1999)]
[Rules and Regulations]
[Pages 2819-2821]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-909]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-68-AD; Amendment 39-10998; AD 98-24-31]
Airworthiness Directives; Bell Helicopter Textron Canada (BHTC)
Model 430 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 98-24-31, which was sent
previously to all known U.S. owners and operators of BHTC Model 430
helicopters by individual letters. This AD requires, within 10 hours
time-in-service (TIS), inspecting the lateral control tube (control
tube) assembly and the forward fairing assembly for chafing. If chafing
is found, replace the control tube assembly and rework the forward
fairing assembly before further flight. If no chafing is found during
the initial inspection, perform the corrective actions within the next
150 hours TIS. This amendment is prompted by two incidents of binding
of the control tube assembly that occurred during flight. The actions
specified by this AD are intended to prevent binding of the control
tube assembly with the inside surface of the forward fairing assembly
under certain load conditions and subsequent loss of control of the
helicopter.
DATES: Effective February 3, 1999, to all persons except those persons
to whom it was made immediately effective by priority letter AD 98-24-
31, issued on November 19, 1998, which contained the requirements of
this amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 3, 1999.
Comments for inclusion in the Rules Docket must be received on or
before March 22, 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-68-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
The applicable service information 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; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mike Kohner, Aerospace Engineer, FAA,
Rotorcraft Directorate, Rotorcraft Certification Office, ASW-170, 2601
Meacham Blvd., Fort Worth, Texas, 76137, telephone (817) 222-5447, fax
(817) 222-5783.
SUPPLEMENTARY INFORMATION: On November 19, 1998, the FAA issued
priority letter AD 98-24-31, applicable to BHTC Model 430 helicopters,
which requires, within 10 hours TIS, inspecting the control tube
assembly and the forward fairing assembly for chafing. If chafing is
found, the AD requires replacing the control tube assembly and
reworking the forward fairing assembly before further flight. If no
chafing is found during the initial inspection, the AD requires the
corrective actions be accomplished within the next 150 hours TIS.
Replacing the control tube assembly and reworking the forward fairing
assembly as prescribed in this AD constitute terminating action for the
requirements of this AD. That action was prompted by two incidents of
binding of the control tube assembly that occurred during flight. This
condition, if not corrected, could result in binding of the control
tube assembly with the inside surface of the forward fairing assembly
under certain load conditions and subsequent loss of control of the
helicopter.
The FAA has reviewed Bell Helicopter Textron Alert Service Bulletin
No. 430-98-6, dated June 12, 1998, which describes procedures for
replacing the control tube assembly and reworking the forward fairing
assembly. Additionally, Transport Canada, which is the Airworthiness
Authority for Canada, has issued AD CF-98-29, dated August 31, 1998, to
mandate these actions.
Since the unsafe condition described is likely to exist or develop
on other BHTC Model 430 helicopters of the same type design, the FAA
issued priority letter AD 98-24-31 to prevent binding of the control
tube assembly with the inside surface of the forward fairing assembly
under certain load conditions and subsequent loss of control of the
helicopter. The AD requires, within 10 hours TIS, inspecting the
control tube assembly, part number (P/N) 430-001-018-101, and the
forward fairing assembly, P/N 430-061-822-101, for chafing between the
inner surface of the forward fairing assembly and the top surface of
the control tube assembly. If chafing is found, replacing the control
tube assembly with an airworthy control tube assembly, P/N 430-001-018-
113, and reworking the forward fairing assembly is required before
further flight. If no chafing is found during the initial inspection,
these corrective actions are required within the next 150 hours TIS.
Replacing the control tube assembly and reworking the forward fairing
assembly as prescribed in this AD constitute terminating action for the
requirements
[[Page 2820]]
of this AD. The actions are required to be accomplished in accordance
with the service bulletin described previously. The short compliance
time involved is required because the previously described critical
unsafe condition can adversely affect the controllability of the
helicopter. Therefore, inspecting the control tube assembly and the
forward fairing assembly for chafing is required within 10 hours TIS,
and this AD must be issued immediately.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on November 19, 1998, to all known U.S. owners and operators of
BHTC Model 430 helicopters. These conditions still exist, and the AD is
hereby published in the Federal Register as an amendment to section
39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it
effective to all persons.
The FAA estimates that 12 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 12 work hours per
helicopter to accomplish the required actions, and that the average
labor rate is $60 per work hour. Required parts will cost approximately
$1,870 per helicopter. Based on these figures, the total cost impact of
the AD on U.S. operators is estimated to be $31,080, assuming the
control tube assembly is replaced in the entire U.S. fleet.
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-68-AD.'' The postcard will be date stamped and
returned to the commenter.
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 98-24-31 Bell Helicopter Textron Canada: Amendment 39-10998.
Docket No. 98-SW-68-AD.
Applicability: Model 430 helicopters, serial numbers 49001
through 49018, 49020 through 49036, and 49038, 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 use the authority
provided in paragraph (e) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent binding of the lateral control tube (control tube)
assembly with the inside surface of the forward fairing assembly
under certain load conditions and subsequent loss of control of the
helicopter, accomplish the following:
(a) Within 10 hours time-in-service (TIS), inspect for chafing
between the inner surface of the forward fairing assembly, part
number (P/N) 430-061-822-101, and the top surface of the control
tube assembly, P/N 430-001-018-101.
(b) If any chafing is found, prior to further flight, replace
the control tube assembly with an airworthy control tube assembly,
P/N 430-001-018-113, and rework the forward fairing assembly, P/N
430-061-822-101. This reworking and replacing must be accomplished
in accordance with Part II of the Accomplishment Instructions of
Bell Helicopter Textron Alert Service Bulletin No. 430-98-6, dated
June 12, 1998 (ASB), except that contact with PSE is not required.
(c) If no chafing is found during the inspection in paragraph
(a), within the next 150 hours TIS, replace the control tube
assembly with an airworthy control tube assembly, P/N 430-001-018-
113, and rework the forward fairing assembly in accordance with Part
II of the Accomplishment Instructions of the ASB.
(d) Replacing the control tube assembly, P/N 430-001-018-101,
with an airworthy control tube assembly, P/N 430-001-018-113, and
reworking the forward fairing assembly as prescribed by this AD
constitute terminating action for the requirements of this AD.
[[Page 2821]]
(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 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 replacing of the control tube assembly and the reworking
of the forward fairing assembly shall be done in accordance with
Bell Helicopter Textron Alert Service Bulletin No. 430-98-6, dated
June 12, 1998. This incorporation by reference was 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 February 3, 1999, to all
persons except those persons to whom it was made immediately
effective by Priority Letter AD 98-24-31, issued November 19, 1998,
which contained the requirements of this amendment.
Note 3: The subject of this AD is addressed in Transport Canada
(Canada) AD CF-98-29, dated August 31, 1998.
Issued in Fort Worth, Texas, on January 7, 1999.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 99-909 Filed 1-15-99; 8:45 am]
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