[Federal Register Volume 62, Number 196 (Thursday, October 9, 1997)]
[Rules and Regulations]
[Pages 52653-52655]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-26623]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 62, No. 196 / Thursday, October 9, 1997 /
Rules and Regulations
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-SW-24-AD; Amendment 39-10152; AD 97-15-16]
RIN 2120-AA64
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) 97-15-16, which was sent
previously to all known U.S. owners and operators of BHTC Model 430
helicopters by individual letters. This AD requires inspections of all
4 main rotor adapter assemblies for evidence of flapping contact
between the adapter liners and the upper stop assembly plugs, and for
evidence of lead-lag contact between the adapter pads and the yoke
assembly; installing a never-exceed-velocity (VNE) placard; marking the
airspeed indicator to reflect the airspeed restriction; installing a
slippage mark on the airspeed indicator glass and instrument case; and
inserting revisions to the rotorcraft flight manual to reflect the
airspeed revision. This amendment is prompted by a report of a main
rotor tip path plane separation, which occurred during a ferry flight
at an airspeed of more than 140 knots indicated airspeed (KIAS). The
actions specified by this AD are intended to prevent tip path plane
separation, increased vibrations, possible damage to the main rotor
system, and subsequent loss of control of the helicopter.
DATES: Effective October 24, 1997, to all persons except those persons
to whom it was made immediately effective by priority letter AD 97-15-
16, issued on July 18, 1997, 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 October 24, 1997.
Comments for inclusion in the Rules Docket must be received on or
before December 8, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 97-SW-24-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 Assistant Chief Counsel, 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: Mr. 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: On July 18, 1997, the FAA issued priority
letter AD 97-15-16, applicable to BHTC Model 430 helicopters, which
requires inspections of all 4 main rotor adapter assemblies for
evidence of flapping contact between the adapter liners and the upper
stop assembly plugs, and for evidence of lead-lag contact between the
adapter pads and the yoke assembly; installing a VNE placard; marking
the airspeed indicator to reflect the airspeed restriction; installing
a slippage mark on the airspeed indicator glass and instrument case;
and inserting revisions to the rotorcraft flight manual to reflect the
airspeed revision. That action was prompted by one report of a main
rotor tip path plane separation, which occurred during a ferry flight
at an airspeed of more than 140 KIAS. The separation was observed from
the cockpit and caused a vibration at a frequency near one per
revolution. BHTC was able to reproduce a similar event on other Model
430 helicopters, and determined that the separation may occur at
airspeeds above 120 KIAS. Therefore, flight at airspeeds above 120 KIAS
is considered unsafe. This condition, if not corrected, could result in
tip path plane separation, increased vibrations, possible damage to the
main rotor system, and subsequent loss of control of the helicopter.
The FAA has reviewed Bell Helicopter Textron Alert Service Bulletin
(ASB) No. 430-97-2, dated July 11, 1997, which describes inspections of
all 4 main rotor adapter assemblies for evidence of flapping contact
between the adapter liners and the upper stop assembly plugs; and, for
evidence of lead-lag contact between the adapter pads and the yoke
assembly. The ASB also describes further inspections if evidence of
contact is found during either of those inspections. For helicopters
equipped with skid landing gear, removing the existing VNE placard and
installing a VNE placard, part number (P/N) 430-075-208-107, is
required; and for helicopters equipped with retractable landing gear,
removing the existing VNE placard and installing a VNE placard, P/N
430-075-208-109, is required. Finally, the ASB describes marking the
airspeed indicators to reflect the airspeed restriction by adding to
the instrument glass a red arc to indicate that airspeeds above 120
KIAS are prohibited; and inserting revisions to the rotorcraft flight
manual that reflect this airspeed restriction.
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 97-15-16 to prevent tip path plane
separation, increased vibrations, possible damage to the main rotor
system, and subsequent loss of control of the helicopter. The AD
requires, before further flight, inspections of all 4 main rotor
adapter assemblies for evidence of flapping contact between the adapter
liners and the upper stop assembly plugs, and for evidence of lead-lag
contact between the adapter pads and the yoke assembly. Flapping
contact is indicated by scrubbing (or smudging) of the adapter liner
surface, characteristic of relative motion between the surfaces of the
adapter liners and upper stop assembly plugs. Lead-lag contact is
indicated by
[[Page 52654]]
a permanent indentation or split in the surface of the adapter pads.
Further inspections are required if evidence of contact is found during
either of those inspections. For helicopters equipped with skid landing
gear, this AD requires the removing the existing VNE placard and
installing a VNE placard, P/N 430-075-208-107; and for helicopters
equipped with retractable landing gear, removing the existing VNE
placard and installing a VNE placard, P/N 430-075-208-109, is required.
Finally, this AD requires marking each airspeed indicator to reflect
the airspeed restriction by adding to the instrument glass a red arc to
indicate that airspeeds above 120 KIAS are prohibited; installing a
slippage mark on each airspeed indicator glass and instrument case; and
inserting revisions to the rotorcraft flight manual that reflect the
airspeed restriction. The actions are required to be accomplished in
accordance with the service bulletin described previously.
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 July 18, 1997 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 Sec. 39.13
of the Federal Aviation Regulations (14 CFR 39.13) to make it effective
to all persons.
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 concernedwith 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. 97-SW-24-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:
97-15-16 Bell Helicopter Textron Canada: Amendment 39-10152. Docket
No. 97-SW-24-AD.
Applicability: Model 430 helicopters, 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 (g) 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 before further flight, unless accomplished
previously.
To prevent tip path plane separation, increased vibrations,
possible damage to the main rotor system, and subsequent loss of
control of the helicopter, accomplish the following:
(a) Inspect all 4 main rotor adapter assemblies for evidence of
flapping contact between the adapter liners and the upper stop
assembly plugs. Refer to Figures 1, 2, and 3 of the Accomplishment
Instructions of Bell Helicopter
Textron Canada (BHTC) Alert Service Bulletin (ASB) No. 430-97-2,
dated July 11, 1997. Flapping contact is indicated by scrubbing (or
smudging) of the adapter liner surface, characteristic of relative
motion between the surfaces of the adapter lines and upper stop
assembly plugs.
(b) Inspect all 4 main rotor adapter assemblies for evidence of
lead-lag contact between the adapter pads and the yoke assembly.
Refer to Figures 1 and 2 of the Accomplishment Instructions of BHTC
ASB No. 430-97-2, dated July 11, 1997. Lead-lag contact is indicated
by a permanent indentation or split in the surface of the adapter
pads.
(c) If the inspections in paragraphs (a) or (b) of this AD
reveal that there has been contact, inspect and replace the main
rotor yoke and stop assemblies in accordance with Part I, No. 3 of
the Accomplishment Instructions of BHTC ASB No. 430-97-2, dated July
11, 1997.
(d) For helicopters equipped with skid landing gear or
retractable landing gear,
[[Page 52655]]
remove the existing never-exceed-velocity (VNE) placard from the
overhead console and install VNE placard, P/N 430-075-208-107, or P/
N 430-075-208-109, as applicable, in accordance with Part II, of the
Accomplishment Instructions of BHTC ASB No. 430-97-2, dated July 11,
1997.
(e) Install on each airspeed indicator a red arc between 120
knots and 150 knots to indicate that airspeeds above 120 knots
indicated airspeed are prohibited. Install a slippage mark on each
airspeed indicator glass and instrument case.
(f) Insert the temporary revisions, BHT-430-FM-1 and BHT-430-
FMS-1, as appropriate, both dated July 7, 1997, into the rotorcraft
flight manual.
(g) 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.
(h) Special flight permits will not be issued.
(i) The inspections and installations shall be done in
accordance with Bell Helicopter Textron Alert Service Bulletin (ASB)
No. 430-97-2, dated July 11, 1997. 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 Assistant Chief Counsel,
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.
(j) This amendment becomes effective on October 24, 1997, to all
persons except those persons to whom it was made immediately
effective by priority letter AD 97-15-16, issued July 18, 1997,
which contained the requirements of this amendment.
Issued in Fort Worth, Texas, on September 26, 1997.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 97-26623 Filed 10-8-97; 8:45 am]
BILLING CODE 4910-13-U
