AD Amdt-39-9210

[Federal Register Volume 60, Number 89 (Tuesday, May 9, 1995)]
[Rules and Regulations]
[Pages 24553-24555]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 95-11223]




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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-SW-16-AD; Amendment 39-9210; AD 95-09-07]


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 amendment adopts a new airworthiness directive (AD) that 
is applicable to Robinson Helicopter Company Model R44 helicopters. 
This action requires removal of the push-pull tube sleeve guide 
assembly (sleeve guide) and replacement with a push-pull tube roller 
guide assembly (roller guide); and, inspections of the push-pull tube 
sleeves for signs of wear and replacement as necessary. This amendment 
is prompted by a report of an operator experiencing binding in the 
cyclic control system caused by torn heat-shrink material (material) on 
the cyclic push-pull tubes binding in the sleeve guide. The actions 
specified in this AD are intended to prevent binding in the cyclic 
control system and subsequent loss of control of the helicopter.

DATES: Effective May 24, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 24, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before July 10, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 95-SW-16-AD, 2601 Meacham Blvd., Fort Worth, Texas 
76137.
    The service information referenced in this AD may be obtained from 
Robinson Helicopter Company, 2901 Airport Drive, Torrance, California 
90505. 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: Ms. Lirio Liu, Aerospace Engineer, 
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Blvd., 
Lakewood, [[Page 24554]] California 90712, telephone (310) 627-5229, 
fax (310) 627-5210.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD that is 
applicable to Robinson Model R44 helicopters. The Civil Aviation 
Authority of England reported that on October 11, 1994, an operator of 
a Model R44 helicopter experienced binding in the cyclic control 
system. An inspection revealed that the material on the cyclic control 
push-pull tubes had torn and caused the push-pull tubes to bind in the 
push-pull tube guide. After reviewing this report, as well as the 
manufacturer's data on wear-testing of the material used on the push-
pull tube, and the maintenance history of the wear of this material at 
the existing sleeve guide, the FAA has determined that the existing 
sleeve guide should be replaced with a roller guide within the next 25 
hours time-in-service (TIS) in order to reduce the wear on the push-
pull tube material, and preserve the integrity of the cyclic control 
system. The cyclic control system controls the attitude of the 
helicopter. If it binds, the operator loses the ability to control 
inputs to the main rotor. Due to the criticality of the cyclic control 
system and the relatively short compliance time, this rule must be 
issued immediately to correct an unsafe condition in the affected 
helicopters. This condition, if not corrected, could result in binding 
in the cyclic control system and subsequent loss of control of the 
helicopter.
    The FAA has reviewed Robinson Helicopter Company R44 Service 
Bulletin SB-4 (SB), dated January 24, 1995, which describes procedures 
for removal of the existing sleeve guide and replacement with a roller 
guide within the next 50 hours TIS. It also describes procedures for 
inspecting the push-pull sleeve tube for signs of wear, and replacement 
as necessary. However, based upon the manufacturer's test data as well 
as the TIS of the helicopter that was involved in the one reported 
incident (56.5 hours TIS), the FAA has determined that a compliance 
time of 25 hours TIS is necessary to ensure the safety of the affected 
helicopters.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other Robinson Model R44 helicopters of the same 
type design, this AD is being issued to prevent binding in the cyclic 
control system and subsequent loss of control of the helicopter. This 
AD requires removal of the sleeve guide and replacement with a roller 
guide. This AD also requires an initial inspection and repetitive 
inspections at 100 hours TIS intervals of the C121-7 push-pull tube 
sleeve for signs of wear, and replacement as necessary. The actions are 
required to be accomplished in accordance with the service bulletin 
described previously.
    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. 95-SW-16-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. 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 adding a new airworthiness directive 
to read as follows:

95-09-07  Robinson Helicopter Company: Amendment 39-9210. Docket No. 
95-SW-16-AD.

    Applicability: Model R44 helicopters, serial numbers (S/N) 0001 
through 0150, 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 (c) 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 [[Page 24555]] 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 in the cyclic control system and subsequent 
loss of control of the helicopter, accomplish the following:
    (a) Within 25 hours time-in-service after the effective date of 
this AD, remove the existing push-pull tube sleeve guide assembly 
(sleeve guide) and replace it with a C439-7 push-pull tube roller 
guide assembly (roller guide), which is included in the KI-88 push-
pull tube guide kit, in accordance with the Compliance Procedure in 
Robinson Helicopter Company Service Bulletin SB-4, dated January 24, 
1995.
    (b) Inspect the C121-7 push-pull tube sleeve for signs of wear 
and replace, if necessary, using the sleeves and adhesive in the KI-
88 push-pull tube guide kit in accordance with the Compliance 
Procedure in Robinson Helicopter Company Service Bulletin SB-4, 
dated January 24, 1995. Repeat this inspection at each 100 hours TIS 
in accordance with the applicable maintenance manual.
    (c) 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, 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.

    (d) 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.
    (e) The removal and replacement shall be done in accordance with 
Robinson Helicopter Company Service Bulletin SB-4, dated January 24, 
1995. 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. 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.
    (f) This amendment becomes effective on May 24, 1995.

    Issued in Fort Worth, Texas, on May 1, 1995.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-11223 Filed 5-8-95; 8:45 am]
BILLING CODE 4910-13-P