[Federal Register Volume 60, Number 174 (Friday, September 8, 1995)]
[Proposed Rules]
[Pages 46790-46792]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-22338]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-SW-16-AD]


Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
206A and 206B Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of Proposed Rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to Bell Helicopter Textron, 
Inc. (BHTI) Model 206A and 206B helicopters, that currently requires an 
inspection of the main transmission input driveshaft assembly 
(driveshaft) at intervals of 300 hours time-in-service (TIS); the 
application of a zinc chromate primer inspection visual aid; and, daily 
visual checks of the driveshaft. This action would require inspections 
of the driveshaft at intervals of 300 hours TIS; the application of a 
self-adhesive temperature indicator visual inspection aid; and, 
preflight visual owner/operator (pilot) checks of the driveshaft. This 
proposal is prompted by recent studies that indicate that self-adhesive 
temperature indicators are a more reliable means of detecting overheat 
conditions on grease-lubricated couplings than the zinc chromate 
primers that are currently in use. The actions specified by the 
proposed AD are intended to prevent failure of the driveshaft due to 
coupling wear or overheating, which could result in loss of power to 
the main rotor and a subsequent forced emergency landing.

DATES: Comments must be received by November 7, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Assistant Chief Counsel, Attention: 
Rules Docket No. 94-SW-16-AD, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137. Comments may be inspected at this location between 9:00 
a.m. and 3:00 p.m., Monday through Friday, except Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Bell Helicopter Textron, Inc., Product Support Dept., 
P.O. Box 482, Fort Worth, Texas 76101. This information may be examined 
at the FAA, Office of the Assistant Chief Counsel, 2601 Meacham Blvd., 
Room 663, Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT: Mr. Jurgen Priester, Aerospace 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5159; fax (817) 222-
5959.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket No. 94-SW-16-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Office of the Assistant Chief Counsel, Attention: Rules 
Docket No. 94-SW-16-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 
76137.

Discussion

    On January 26, 1981, the FAA issued AD 81-04-08, Amendment 39-4037 
(46 FR 12469, February 17, 1981), to require an inspection of the 
driveshaft at intervals of 300 hours TIS; the application of a zinc 
chromate primer 

[[Page 46791]]
inspection visual aid; and, daily visual checks of the driveshaft that 
may be performed by the pilot. That action was prompted by reports of 
excessive wear and failures of the driveshaft. The requirements of that 
AD are intended to prevent failure of the driveshaft due to coupling 
wear or overheating, which would result in loss of power to the main 
rotor and a forced emergency landing.
    Since the issuance of that AD, manufacturer's studies have shown 
that self-adhesive temperature indicators are a more reliable means of 
detecting overheat conditions on grease-lubricated couplings than zinc 
chromate primers. BHTI has issued Alert Service Bulletin (ASB) No. 206-
93-76, Revision B, dated September 6, 1994, which describes procedures 
for the application of a self-adhesive temperature indicator, as well 
as for repetitive visual checks of the driveshaft for grease leakage 
from the grease-lubricated couplings, overheating, and security of the 
clamps and bolts used to attach the driveshaft to transmission and 
engine couplings. The checks described in this proposal before the 
first flight of each day may be performed by a pilot, but must be 
entered into the aircraft records showing compliance with the AD in 
accordance with sections 43.11 and 91.417(a)(2)(v) of the Federal 
Aviation Regulations. This notice proposes to allow a pilot to perform 
these checks because they involve only a visual check for grease 
leakage, overheating, and security of the clamps and bolts used to 
attach the driveshaft to transmission and engine couplings. These 
checks can be performed equally well by a pilot or a mechanic. They 
involve checking items similar to those items that a pilot checks 
during a preflight check. This notice proposes that a mechanic inspect 
the driveshaft and driveshaft couplings at intervals of 300 hours TIS.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other BHTI Model 206A and 206B helicopters of the 
same type design, the proposed AD would supersede AD 81-04-08 to 
require inspections of the driveshaft at intervals of 300 hours TIS; 
the application of a self-adhesive visual over-temperature indicator; 
and, preflight visual pilot checks of the driveshaft. The actions would 
be accomplished in accordance with BHTI ASB No. 206-93-76, Revision B, 
dated September 6, 1994, described previously.
    The FAA estimates that 4,312 helicopters of U.S. registry would be 
affected by this proposed AD, that it would take approximately one and 
one-half work hours per helicopter to accomplish the proposed actions, 
and that the average labor rate is $60 per work hour. Required parts 
would be provided by the manufacturer at no charge, but installation 
materials would cost approximately $10 per helicopter. Based on these 
figures, the total cost impact of the proposed AD on U.S. operators is 
estimated to be $431,200.
    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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act. A copy of the draft regulatory 
evaluation prepared for this action is contained in the Rules Docket. A 
copy of it may be obtained by contacting 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.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-4037 (46 FR 
12469, February 17, 1981), and by adding a new airworthiness directive 
(AD), to read as follows:

Bell Helicopter Textron, Inc.: Docket No. 94-SW-16-AD. Supersedes AD 
81-04-08, Amendment 39-4037.

    Applicability: Model 206A and 206B 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 (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 failure of the main transmission input driveshaft 
assembly (driveshaft) due to coupling wear or overheating, which 
could result in loss of power to the main rotor and a subsequent 
forced emergency landing, accomplish the following:
    (a) Before the first flight of each day after the effective date 
of this AD, visually check the driveshaft, part number (P/N) 206-
040-100-13, for: (1) Grease leakage from the driveshaft coupling, P/
N 206-040-108-005; and (2) visual damage and security of the clamps 
and bolts used to attach the driveshaft to the transmission and 
engine couplings. After compliance with paragraph (d) of this AD, 
also check the self-adhesive visual over-temperature indicators 
(over-temperature indicators) for overheating, deterioration, 
debonding, or discoloration in accordance with Part II of the 
Accomplishment Instructions of Bell Helicopter Textron, Inc. (BHTI) 
Alert Service Bulletin (ASB) No. 206-93-76, Revision B, dated 
September 6, 1994. If any grease leakage exists, or if there are 
indications of overheating, disassemble and inspect the driveshaft 
in accordance with the applicable maintenance manual, and replace 
the over-temperature indicators in accordance with Part III of the 
Accomplishment Instructions of BHTI ASB 206-93-76, Revision B, dated 
September 6, 1994.
    (b) The visual check required by paragraph (a) may be performed 
by an owner/operator (pilot) holding at least a private pilot 
certificate, and must be entered into the aircraft records showing 
compliance with this AD in accordance with sections 43.11 and 
91.417(a)(2)(v) of the Federal Aviation Regulations.
    (c) Inspect and lubricate the driveshaft assembly, P/N 206-040-
100-13, and driveshaft grease-lubricated couplings, P/N 206-040-108-
005, in accordance with the helicopter's maintenance manual and 
according to the compliance schedule that follows, and thereafter, 
inspect and lubricate at intervals not to exceed 300 hours time-in-
service (TIS):
    (1) For helicopters with 250 hours TIS or more, compliance is 
required within the next 50 hours TIS; or, 

[[Page 46792]]

    (2) For helicopters with less than 250 hours TIS, compliance is 
required prior to attaining 300 hours TIS.
    (d) Install the over-temperature indicators at the next 300 
hours TIS driveshaft coupling inspection and lubrication in 
accordance with Part I of the Accomplishment Instructions of BHTI 
ASB 206-93-76, Revision B, dated September 6, 1994.
    (e) 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, 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.

    (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.

    Issued in Fort Worth, Texas, on August 31, 1995.
Daniel P. Salvano,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-22338 Filed 9-7-95; 8:45 am]
BILLING CODE 4910-13-P