[Federal Register Volume 78, Number 80 (Thursday, April 25, 2013)]
[Proposed Rules]
[Pages 24368-24371]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-09764]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0379; Directorate Identifier 2009-SW-26-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. (Bell)
Model Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede an existing revised airworthiness
directive (AD) for all Bell Model 204B and certain serial-numbered
Model 205A-1 helicopters with a certain tail rotor pitch control chain
(chain) installed. The existing AD requires visually inspecting the
chain to detect a crack in the link segments and, for affected Model
205A-1 helicopters, replacing the tail rotor chain and cable control
system with a push-pull control system. Since we issued that AD, we
have determined the need to apply the requirements to a newly-produced,
similarly-designed chain with a different part number. Also, for the
Model 204B, data shows the need to reduce the inspection interval of
the chain and revise its inspection procedures because the rapid growth
of a crack can lead to premature chain failure and to install a tail
rotor cable and chain damper kit (damper kit) to reduce the oscillatory
loading. We have also determined that installing a push-pull control
system should apply to Model 205A-1 helicopters with
[[Page 24369]]
certain serial numbers, regardless of the chain part number installed.
These proposed actions are intended to prevent failure of the chain,
loss of tail rotor blade pitch control, and subsequent loss of control
of the helicopter.
DATES: We must receive comments on this proposed AD by June 24, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the economic
evaluation, any comments received, and other information. The street
address for the Docket Operations Office (telephone 800-647-5527) is in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
For service information identified in this proposed AD, contact
Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101,
telephone (817) 280-3391, fax (817) 280-6466, or at http://www.bellcustomer.com/files/. You may review a copy of the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, ASW-170, Aviation
Safety Engineer, Rotorcraft Directorate, Rotorcraft Certification
Office, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817)
222-5170, fax (817) 222-5783, email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
On June 3, 1976, we issued AD 76-12-07, Amendment 39-2640 (41 FR
23939, June 14, 1976), Docket No. 76-SW-19. That AD required repetitive
inspections, at intervals not to exceed 25 hours time-in-service (TIS),
for a chain, part number (P/N) 204-001-739-003, installed on Bell Model
204B and 205A-1 helicopters. This AD also required, before further
flight, replacing chains with cracked or broken links or segments.
On September 12, 1979, we revised AD 76-12-07 by issuing Amendment
39-3569 (44 FR 55555, September 27, 1979). That amendment limits the
applicability for the Model 205A-1 helicopter to those with a serial
number (S/N) of 30001 through 30228; decreases the inspection interval
of the chain from 25 hours TIS to 10 hours TIS; and requires replacing
the existing chain and cable control system with a push-pull control
system.
Both amendments were prompted by several chain failures occurring
in flight and reports of cracked chain links on Model 205A-1
helicopters. Those actions are intended to detect cracks in the chain
link segments to prevent failure of a chain and subsequent loss of
directional control of the helicopter.
Actions Since Existing ADs Were Issued
Since we issued the original (June 3, 1976) and revised (September
12, 1979) versions of AD 76-12-07, we have approved a very-similarly
designed chain, P/N 204-001-739-105, eligible for installation on Model
204B helicopters. Testing by the manufacturer has shown that the
fatigue characteristics for the two chains are almost identical, and
the requirements of AD 76-12-07 should apply to this additional part-
numbered chain. Also, we have determined that this crack can grow
quickly, and thus the recurring inspection interval for the Model 204B
should be reduced from 25 hours TIS to 10 hours TIS and should include
procedures to slowly operate the cockpit anti-torque control pedals
during the inspection. This is so that the entire surface area of the
chain in contact with the control quill sprocket (sprocket), including
that portion underneath the sprocket, can be inspected. Testing has
also shown a reduction in the oscillatory loading of the chain when a
damper kit is installed. To complement these requirements, we have
determined for the Model 204B that we should revise the Airworthiness
Limitations section of the maintenance manual, or the Instructions for
Continued Airworthiness (ICAs), to include the 10 hours TIS recurring
inspection.
We have also determined that the requirement in AD 76-12-07 for the
Model 205A-1 to replace the tail rotor chain and cable control system
with a push-pull control system should apply regardless of chain part
number installed. This would be required before further flight to
ensure that any part-numbered chain cannot be installed on a Model
205A-1 helicopter, which should already have a push-pull control system
installed in accordance with the requirement in AD 76-12-07. The
actions in this proposed AD are intended to prevent failure of the
chain, loss of tail rotor blade pitch control, and subsequent loss of
control of the helicopter.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other helicopters of these same type
designs.
Related Service Information
The FAA has reviewed Bell Alert Service Bulletin (ASB) No. 204-75-
4, dated December 16, 1975, for the Model 204B helicopter, which
specifies to visually inspect the chain using a 10-power magnifying
glass every 10 flight hours. The inspection intervals for a chain were
reduced because of several field reports of cracked and broken links.
We have also reviewed Bell ASB 204-79-7, dated August 21, 1979,
[[Page 24370]]
which specifies the installation of a damper kit. A field evaluation
has shown considerable improvement in the reliability of the chain when
a damper kit is installed.
Further, we have reviewed Bell ASB No. 205-78-5, dated May 16,
1978, for Model 205A-1 helicopters, serial number 30001 through 30228,
which specifies removing the tail rotor chain and cable control system
and installing a push-pull control system kit, P/N 205-704-057-001 or
205-704-057-101. The tail rotor push-pull control system is installed
in accordance with Service Instructions (SI) No. 205-38, ``changed''
March 28, 1990, for an improved tail rotor hub and blade assembly kit,
P/N 205-704-040-001 and 205-704-040-003, and SI No. 205-46, revised
March 7, 1980, for installing a push/pull anti-torque retrofit kit.
Proposed AD Requirements
The proposed AD would require:
For Bell Model 205A-1 helicopters, S/N 30001 through
30228, before further flight, replacing the tail rotor chain and cable
control system with an airworthy tail rotor push-pull control system by
installing an improved tail rotor hub and blade assembly kit, P/N 205-
704-040-001 or 205-704-040-003, and then installing a push/pull anti-
torque retrofit kit, P/N 205-704-057-001 or 205-704-057-101.
For Bell Model 204B helicopters, visually inspecting
chains, P/N 204-001-739-003 and -105, at 10-hour TIS intervals using a
10-power or higher magnifying glass and a light; revising the
inspection procedures; installing a damper kit; and revising the
maintenance manual or ICAs to include the inspection intervals.
Costs of Compliance
We estimate that this proposed AD would affect 13 Model 204B and 52
Model 205A-1 helicopters of U.S. registry and that operators may incur
the following costs:
Visual inspection of the link segments in a chain on a
Model 204B helicopter will require .25 work hour for each inspection,
60 per year, at an average labor rate of $85 per work hour for a cost
per helicopter of $1,275 and fleet cost of $16,575;
Replacement of a chain having a cracked or broken link or
segment on a Model 204B helicopter would require .5 work hour and a
parts cost of $4,922, for a cost per helicopter of $4,965 and a total
cost of $9,930 (assuming 2 would be replaced);
Installation of a damper kit on a Model 204B helicopter
would require 3 work hours and a parts cost of $14,925, for a cost per
helicopter of $15,180 and a total cost of $30,360 (assuming 2 would be
installed); and
Installation of a tail rotor push-pull control system on
an affected Model 205A-1 helicopter would require 225 work hours and a
parts cost of $152,214, for a cost per helicopter of $171,339.
Therefore, we estimate the total cost impact of the proposed AD on
U.S. operators to be $228,204.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect 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.
For the reasons discussed, I certify 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);
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
4. 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.
We prepared an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
Reference, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-3569 (44 FR
55555, September 27, 1979), which amended Amendment 39-2640 (41 FR
23939; June 14, 1976), and by adding the following new airworthiness
directive (AD):
Bell Helicopter Textron (Bell): Docket No. FAA-2013-0379;
Directorate Identifier 2009-SW-26-AD.
(a) Applicability
This AD applies to Model 204B helicopters with a tail rotor
pitch control chain (chain), part number (P/N) 204-001-739-003 or -
105, installed, and Model 205A-1 helicopters with a serial number
(S/N) 30001 through 30228, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a chain,
which can grow quickly because of oscillatory loads and lead to
premature failure of the chain, loss of the tail rotor blade pitch
control, and subsequent loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 76-12-07, Amendment 39-2640 (41 FR 23939,
June 14, 1976) as revised by Amendment 39-3569 (44 FR 55555,
September 27, 1979).
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) For Model 205A-1 helicopters, before further flight, replace
the tail rotor chain and cable control system with an airworthy tail
rotor push-pull control system by installing an improved tail rotor
hub and blade assembly kit, P/N 205-704-040-001 or 205-704-040-103,
and then installing a push/pull anti-torque retrofit kit, P/N 205-
704-057-001 or 205-704-057-101.
(2) For Model 204B helicopters:
(i) Within 10 hours time-in-service (TIS) and thereafter at
intervals not to exceed 10 hours TIS, using a 10-power or higher
magnifying glass and a light, visually inspect
[[Page 24371]]
each of the link segments in the chain for a crack. Also, slowly
operate the cockpit anti-torque control pedals during the inspection
so that the entire surface area of the chain in contact with the
control quill sprocket (sprocket) is visibly accessible and can be
inspected. Pay particular attention to the portion of the chain that
travels over the sprocket and extends 6 inches to each side of the
sprocket.
(A) If there is no cracked or broken link segment, lubricate the
chain with a light preservative oil (C-125) or wipe with a cloth
dampened in lubricating oil (C-010).
(B) If there is a cracked or broken link segment, before further
flight, replace the chain with an airworthy chain.
(ii) Within 50 hours TIS, install a tail rotor cable and chain
damper kit, P/N 204-706-130-101, as depicted in Figures 1 through 3,
and by following the Accomplishment Instructions, paragraphs 2.
through 9., of Bell Alert Service Bulletin (ASB) No. 204-79-7, dated
August 21, 1979.
(f) Alternative Methods of Compliance (AMOC)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to Michael Kohner,
ASW-170, Aviation Safety Engineer, Rotorcraft Directorate, 2601
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5170,
fax (817) 222-5783, email [email protected].
(2) For operations conducted under 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(g) Additional Information
(1) Bell Alert Service Bulletin (ASB) No. 204-75-4, dated
December 16, 1975, and Bell ASB No. 205-78-5, dated May 16, 1978,
which are not incorporated by reference, contain additional
information about the subject of this AD. For this service
information, contact Bell Helicopter Textron, Inc., P.O. Box 482,
Fort Worth, TX 76101, telephone (817) 280-3391, fax (817) 280-6466,
or at http://www.bellcustomer.com/files/. You may review a copy of
the referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in Transport Canada AD
CF-1990-06R1, issued January 7, 2008.
(h) Subject
The Joint Aircraft System Component (JASC) Code is 6720: Tail
Rotor Control System.
Issued in Fort Worth, Texas, on April 18, 2013.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013-09764 Filed 4-24-13; 8:45 am]
BILLING CODE 4910-13-P