Document ID: FAA-2013-0379-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bell Helicopter Textron, Inc. (Bell) Model Helicopters
Posted Date: 2013-04-25T04:00Z

[Federal Register Volume 78, Number 80 (Thursday, April 25, 2013)]
[Proposed Rules]
[Pages 24368-24371]
From the Federal Register Online via the Government Printing 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 mike.kohner@faa.gov.

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 mike.kohner@faa.gov.
    (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