[Federal Register Volume 63, Number 69 (Friday, April 10, 1998)]
[Rules and Regulations]
[Pages 17677-17679]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-9478]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-08-AD; Amendment 39-10461; AD 98-04-12]
RIN 2120-AA64
Airworthiness Directives; Robinson Helicopter Company Model R44
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) 98-04-12 which was sent
previously to all known U.S. owners and operators of Robinson
Helicopter Company (RHC)
[[Page 17678]]
Model R44 helicopters by individual letters. This AD requires an
initial and repetitive measurement of the lateral cyclic trim spring
shaft (shaft) diameter and replacement of the shaft spring assembly
(spring assembly) if the shaft diameter is excessively worn.
Replacement of the spring assembly with a modified spring assembly is
considered terminating action for this AD. This amendment is prompted
by an incident in which a pilot felt binding in the cyclic control when
attempting to move it to the left. A precautionary landing was made
using only right-hand turns. Subsequent inspection revealed that a
notch was worn in the shaft, which caused the shaft and spring to move
from the lower mount and interfere with the lateral control. Inspection
of a second RHC Model 44 helicopter revealed similar wear. Excessive
wear can create a notch on the shaft, which can cause the spring
assembly to move out of its lower mount. This condition, if not
corrected, could lead to the shaft interfering with lateral cyclic
control, which could result in loss of control of the helicopter.
DATES: Effective April 27, 1998, to all persons except those persons to
whom it was made immediately effective by priority letter AD 98-04-12,
issued on February 4, 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 April 27, 1998.
Comments for inclusion in the Rules Docket must be received on or
before June 9, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-08-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
The applicable service information may be obtained from Robinson
Helicopter Company, 2901 Airport Drive, Torrance, California 90505
telephone (310) 539-0508, fax (310) 539-5198. 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: Mr. Fredrick A. Guerin, Aerospace
Engineer, FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Blvd., Lakewood, California 90712, telephone (562)-627-5232,
fax (562)-627-5210.
SUPPLEMENTARY INFORMATION: On February 4, 1998, the FAA issued priority
letter AD 98-04-12, applicable to RHC Model R44 helicopters, which
requires an initial and repetitive measurement of the shaft diameter,
and replacement of the spring assembly if the shaft diameter is
excessively worn. That action was prompted by an incident in which a
pilot felt binding in the cyclic control when attempting to move it to
the left. A precautionary landing was made using only right-hand turns.
Subsequent inspection revealed that a notch was worn in the shaft,
which caused the shaft and spring to move from the lower mount and
interfere with the lateral control. Inspection of a second RHC Model 44
helicopter revealed similar wear. Excessive wear can create a notch on
the shaft, which can cause the spring assembly to move out of its lower
mount. This condition, if not corrected, could lead to the shaft
interfering with lateral cyclic control, which could result in loss of
control of the helicopter.
The FAA has reviewed Robinson Helicopter Company R44 Service
Bulletin SB-26, dated January 31, 1998, which describes procedures for
measurement of the shaft diameter, and replacing the spring assembly
with a modified spring assembly if the shaft diameter varies more than
0.004 inch in any 0.50 inch of length.
Since the unsafe condition described is likely to exist or develop
on other RHC Model R44 helicopters of the same type design, the FAA
issued priority letter AD 98-04-12 to prevent the shaft from
interfering with lateral cyclic control, which could result in loss of
control of the helicopter. The AD requires, within 10 hours time-in-
service (TIS) after the effective date of this AD, and thereafter at
intervals not to exceed 20 hours TIS until replacement of the spring
assembly with a modified spring assembly is accomplished, a measurement
of the shaft diameter; and replacement of the C056-1 Rev. A through G
spring assembly with a C056-1 Rev. H spring assembly if the shaft
diameter measurement varies more than 0.004 inch in any 0.50 inch of
length. Replacement of the C056-1 Rev. A through G spring assembly with
a C056-1 Rev. H spring assembly is considered terminating action for
the requirements of this AD. 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 February 4, 1998 to all known U.S. owners and operators of
RHC Model R44 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.
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-08-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
[[Page 17679]]
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:
98-04-12 Robinson Helicopter Company: Amendment 39-10461. Docket
No. 98-SW-08-AD.
Applicability: Model R44 helicopters, serial numbers 0002
through 0420, 0425, 0426, and 0427, with a C056-1 Rev. A through G
spring assembly installed, 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 (d) 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 detect excessive wear on the lateral cyclic trim spring shaft
(shaft), which could allow the shaft to move from its lower mount
and interfere with lateral cyclic control resulting in loss of
control of the helicopter, accomplish the following:
(a) Within 10 hours time-in-service (TIS), and thereafter at
intervals not to exceed 20 hours TIS, measure the diameter of the
shaft in accordance with the Compliance Procedure contained in
Robinson Helicopter Company R44 Service Bulletin SB-26, dated
January 31, 1998 (SB-26).
(b) If the shaft diameter varies more than 0.004 inch in any
0.50 inch of length, in the measurement area shown in Figure 1 of
SB-26, replace the C056-1 Rev. A through G spring assembly with a
C056-1 Rev. H spring assembly before further flight.
(c) Replacing the C056-1 Rev. A through G spring assembly with a
C056-1 Rev. H spring assembly in accordance with the service
bulletin is considered terminating action for the requirements of
this AD.
(d) 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, Los Angeles Aircraft 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, Los Angeles Aircraft Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles Aircraft Certification Office.
(e) Special flight permits will not be issued.
(f) The inspection shall be done in accordance with the
Compliance Procedure contained in Robinson Helicopter Company R44
Service Bulletin SB-26, dated January 31, 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 Robinson Helicopter Company, 2901 Airport Drive,
Torrance, California 90505, telephone (310) 539-0508, fax (310) 539-
5198. 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.
(g) This amendment becomes effective on April 27, 1998, to all
persons except those persons to whom it was made immediately
effective by Priority Letter AD 98-04-12, issued February 4, 1998,
which contained the requirements of this amendment.
Issued in Fort Worth, Texas, on April 3, 1998.
Henry A. Armstrong,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-9478 Filed 4-9-98; 8:45 am]
BILLING CODE 4910-13-U
