[Federal Register Volume 59, Number 247 (Tuesday, December 27, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-31597]
[[Page Unknown]]
[Federal Register: December 27, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-SW-18-AD; Amendment 39-9105; AD 94-26-10]
Airworthiness Directives; Robinson Helicopter Company Model R44
Series Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Robinson Helicopter Company (RHC) Model R44 series
helicopters, that currently requires removal and replacement of
specific parts of the cyclic control system. This amendment requires
the same removal and replacement of specific parts of the cyclic
control system, corrects a replacement part number, and changes the
applicability to cover certain serial-numbered helicopters. This
amendment is prompted by the need to correct the existing AD by
changing the applicability to include additional serial-numbered
helicopters and to correct a replacement part number that was
incorrectly stated in the existing AD. The actions specified by this AD
are intended to prevent failure of the cyclic control system and
subsequent loss of control of the helicopter.
DATES: Effective January 11, 1995.
Comments for inclusion in the Rules Docket must be received on or
before February 27, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 94-SW-18-AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
FOR FURTHER INFORMATION CONTACT: Ms. Lirio Liu, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, ANM-123L, Transport
Airplane Directorate, 3960 Paramount Blvd., Lakewood, California 90712,
telephone (310) 627-5229, fax (310) 627-5210.
SUPPLEMENTARY INFORMATION: On August 18, 1994, the FAA issued AD 94-17-
18, Amendment 39-9013 (59 FR 43726, August 25, 1994), to require
immediate removal and replacement of specific parts of the cyclic
control system in accordance with the applicable maintenance manual.
That action was prompted by an accident involving an RHC Model R44
series helicopter. The National Transportation Safety Board (NTSB)
determined the probable cause for the accident was fatigue failure of
the cyclic stick assembly, a part of the cyclic control system. The
pilot uses the cyclic control system to control the flight attitude of
the helicopter. If the cyclic control system fails, the pilot loses the
ability to make cyclic control inputs to the main rotor system. After
reviewing the NTSB report, the FAA has determined that certain parts of
the same design as those installed on the accident helicopter need to
be replaced before further flight. That condition, if not corrected,
could result in failure of the cyclic control system and subsequent
loss of control of the helicopter.
Since the issuance of that AD, the FAA has become aware of an error
in the AD. One of the cyclic control system replacement part numbers
was incorrectly stated as C211-3. That part number should have been
part number A211-3. Additionally, that AD should have been applicable
to RHC Model R44 series helicopters, with serial numbers (S/N) less
than but not including S/N 0017, since the manufacturing records
indicate the design changes required by that AD were incorporated by
RHC into the RHC Model R44 production line, beginning with helicopter
S/N 0017. Upon review, the FAA has determined that the original cyclic
control system design meets existing FAA design standards, but has
limited damage tolerance characteristics and does not display slow
crack growth properties. When damaged or flawed, the cyclic stick
assembly can fail due to fatigue prior to its retirement time of 4,000
hours time-in-service.
Since an unsafe condition has been identified that is likely to
exist or develop on other RHC Model R44 series helicopters of the same
type design, this AD supersedes AD 94-17-18 and is being issued to
prevent failure of the cyclic control system and subsequent loss of
control of the helicopter. This AD requires removal and replacement of
certain parts of the cyclic control system of the affected helicopters
as well as changes the applicability of this AD to include certain
serial-numbered helicopters. The actions are required to be
accomplished in accordance with the applicable maintenance manual. Due
to the critical need to (1) ensure the integrity of the cyclic control
system, (2) comply with the requirements of this AD before further
flight, and (3) require replacement of certain parts on certain serial-
numbered helicopters, this rule must be issued immediately to correct
an unsafe condition in the affected helicopters.
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.
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. 94-SW-18-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, 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-9013 (59 FR
43726, August 25, 1994), and by adding a new airworthiness directive
(AD), Amendment 39-9105, to read as follows:
94-26-10 Robinson Helicopter Company: Amendment 39-9105. Docket No.
94-SW-18-AD. Supersedes AD 94-17-18, Amendment 39-9013.
Applicability: Model R44 series helicopters with serial numbers
(S/N) less than but not including S/N 0017, certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the cyclic control system and subsequent
loss of control of the helicopter, accomplish the following:
(a) Before further flight, remove the following cyclic control
system parts and replace them with the corresponding replacement
parts in accordance with the applicable maintenance manual:
Remove part numbers: Replace with part numbers:
A205-3........................... A205-5 Revision J or subsequent FAA-
approved revisions.
C175-1........................... C175-2 Revision H or subsequent FAA-
approved revisions.
C176-1........................... C176-2 Revision B or subsequent FAA-
approved revisions.
C177-1........................... C177-2 Revision F or subsequent FAA-
approved revisions.
C319-1........................... C319-3 Revision I or subsequent FAA-
approved revisions.
C320-1........................... C320-1 Revision L or subsequent FAA-
approved revisions.
C958-4........................... C958-5 Revision E or subsequent FAA-
approved revisions.
A101-4........................... D173-1 Revision A or subsequent FAA-
approved revisions.
C338-1........................... C338-4 Revision C or subsequent FAA-
approved revisions.
A211-2........................... A211-3 Revision I or subsequent FAA-
approved revisions.
A137-1........................... A137-2 Revision C or subsequent FAA-
approved revisions.
(b) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when approved by the Manager, Los Angeles Aircraft
Certification Office. 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: 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.
(c) Special flight permits will not be issued.
(d) This amendment becomes effective on January 11, 1995.
Issued in Fort Worth, Texas, on December 16, 1994.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 94-31597 Filed 12-23-94; 8:45 am]
BILLING CODE 5910-13-P
