[Federal Register Volume 61, Number 56 (Thursday, March 21, 1996)]
[Rules and Regulations]
[Pages 11538-11539]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-6419]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-SW-16-AD; Amendment 39-9541, AD 96-06-04]
Airworthiness Directives; Bell Helicopter Textron, A Division of
Textron Canada, Ltd. Model 206A and 206B Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Bell Helicopter Textron, A Division of Textron
Canada, Ltd., (BHTC) 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 amendment requires
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 amendment is prompted by recent studies that indicate
self-adhesive temperature indicators are a more reliable means of
detecting overheat conditions on grease-lubricated couplings than the
zinc chromate primers currently in use. The actions specified by this
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: Effective April 25, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 25, 1996.
ADDRESSES: The service information referenced in this AD may be
obtained from BHTC, 12,800 Rue de l'Avenir, Mirabel, Quebec, Canada
J7J1R4, ATTN: Product Support Engineering Light Helicopters. 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. 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 81-04-08,
Amendment 39-4037 (46 FR 12469, February 17, 1981), which is applicable
to BHTC Model 206A and 206B helicopters, was published in the Federal
Register on September 8, 1995 (60 FR 46790). That action proposed 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 checks of the driveshaft. The checks described in
the proposal (before the first flight of each day) may be performed by
an owner/operator (pilot), but must be entered into the aircraft
records showing compliance with the preflight check requirements of
this AD in accordance with sections 43.11 and 91.417(a)(2)(v) of the
Federal Aviation Regulations. The notice proposed 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. The notice proposed that a mechanic inspect
the driveshaft and driveshaft couplings at intervals of 300 hours TIS.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. However,
the FAA has reorganized paragraphs (a) and (b) to separate the
requirements of the visual checks that may be performed by the pilot
from the required corrective actions that must be performed by a
mechanic if certain conditions are discovered during the visual check.
The FAA has determined that air safety and the public interest require
the adoption of the rule as proposed with the exception of
organizational changes noted and various editorial changes. The FAA has
determined that these changes will neither increase the economic burden
on any operator nor increase the scope of the AD.
The FAA estimates that 4,312 helicopters of U.S. registry will be
affected by this AD, that it will take approximately one and one-half
work hours per helicopter to accomplish the required actions, and that
the average labor rate is $60 per work hour. Required parts will be
provided by the manufacturer at no charge, but installation materials
will cost approximately $10 per helicopter. Based on these figures, the
total cost impact of the 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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 USC App. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-4037 (46 FR
[[Page 11539]]
12469, February 17, 1981), and by adding a new airworthiness directive
(AD), Amendment 39- , to read as follows:
AD 96-06-04 Bell Helicopter Textron, a Division of Textron Canada,
Ltd.: Amendment 39-9541, 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 couplings,
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 over-temperature indicators (over-
temperature indicators) for overheating, deterioration, debonding,
or discoloration. The visual checks 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
the visual check of this AD in accordance with sections 43.11 and
91.417(a)(2)(v) of the Federal Aviation Regulations.
(b) If any discrepancies are discovered as a result of the
visual check performed in paragraph (a), accomplish the following
before further flight:
(1) If there is any grease leakage or any 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 Bell Helicopter Textron, Inc., Alert
Service Bulletin (ASB) No. 206-93-76, Revision B, dated September 6,
1994.
(2) If any ``dot'' on an over-temperature indicator has changed
color to black, accomplish the corrective action in accordance with
TABLE I and the accompanying Notes in ASB No. 206-93-76, Revision B,
dated September 6, 1994.
(3) If there are any deteriorated, debonded, or discolored over-
temperature indicator(s) that would prevent interpretation of the
indicating ``dots'', replace those over-temperature indicator(s) in
accordance with Part III of the Accomplishment Instructions of ASB
No. 206-93-76, Revision B, dated September 6, 1994. If only one
over-temperature indicator is missing, and no ``dot'' on any other
over-temperature indicator on the same coupling is discolored or
shows mechanical damage or degradation of the epoxy overcoating, the
helicopter may be returned to service.
(4) If there are any loose or damaged clamps or bolts, secure
the loose clamps or bolts and replace the damaged clamps or bolts in
accordance with the applicable maintenance manual.
(c) Inspect and lubricate the driveshaft assembly, P/N 206-040-
100-13, and driveshaft 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,
(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 ASB No.
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.
(g) The inspections, maintenance and installation of over-
temperature indicators shall be done in accordance with ASB No. 206-
93-76, Revision B, dated September 6, 1994. 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, A Division of Textron Canada,
Ltd., 12,800 Rue L'Avenir, Mirabel, Quebec, Canada J7J1R4, ATTN:
Product Support Engineering Light Helicopters. 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.
(h) This amendment becomes effective on April 25, 1996.
Issued in Fort Worth, Texas, on March 11, 1996.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 96-6419 Filed 3-20-96; 8:45 am]
BILLING CODE 4910-13-U
