Document ID: FAA-2011-1188-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bell Helicopter Textron, Inc. (Bell) Helicopters
Posted Date: 2013-01-23T05:00Z

[Federal Register Volume 78, Number 15 (Wednesday, January 23, 2013)]
[Rules and Regulations]
[Pages 4759-4762]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-00985]

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 Rules and Regulations
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  Federal Register / Vol. 78, No. 15 / Wednesday, January 23, 2013 / 
Rules and Regulations  

[[Page 4759]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1188; Directorate Identifier 2008-SW-46-AD; 
Amendment 39-17171; AD 2012-17-08]
RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron, Inc. (Bell) 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding four airworthiness directives related to 
the main rotor yoke (yoke) on the Bell Model 204B, 205A, 205A-1, 205B, 
and 212 helicopters, to retain certain inspections and certain life 
limits, to require an increased inspection frequency for certain yokes, 
and to expand these inspections and retirement lives to other yokes. 
This airworthiness directive is prompted by past reports of cracks in 
the yoke, another recent report of a cracked yoke, and the decision 
that other yokes, approved based on identicality, need to be subject to 
the same inspection requirements and retirement lives. The actions are 
intended to detect a crack in a yoke to prevent failure of the yoke, 
and subsequent loss of control of the helicopter.

DATES: This AD is effective February 27, 2013.

ADDRESSES: For service information identified in this 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.

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 AD, any incorporated-by-reference 
service information, the economic evaluation, any comments received, 
and other information. The street address for the Docket Operations 
Office (phone: 800-647-5527) is U.S. Department of Transportation, 
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5170; 
email 7-avs-asw-170@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On November 2, 2011, at 76 FR 67628, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 to include an AD that would apply to Bell Model 204B, 205A, 
205A-1, 205B, and 212 helicopters, with a yoke, part number (P/N) AAI-
4011-102 (all dash numbers), ASI-4011-102 (all dash numbers), or 204-
011-102 (all dash numbers), installed, certificated in any category. 
That NPRM proposed to supersede four previously-issued ADs for the Bell 
Model 204, 205, and 212 series helicopters: AD 79-20-05, Amendments 39-
3572 (44 FR 55556, September 27, 1979), 39-3626 (44 FR 70123, December 
6, 1979), and 39-3662 (45 FR 6922, January 31, 1980); AD 81-19-01, 
Amendment 39-4207 (46 FR 45595, September 14, 1981); AD 81-19-02, 
Amendment 39-4208 (46 FR 45595, September 14, 1981); and AD 93-05-01, 
Amendment 39-8507 (58 FR 13700, March 15, 1993). Those ADs required 
inspecting certain yokes installed on these helicopters, established 
retirement life limits for these yokes, and required operators to log 
additional hours against the retirement life of the yokes for Model 212 
helicopters conducting more than four external load lifts per hour.
    Since the issuance of those ADs, certain yokes manufactured under a 
parts manufacturer approval (PMA) were identified as being susceptible 
to the same cracking as the Bell manufactured yokes. The NPRM proposed 
retaining the requirements of the existing ADs while expanding the 
applicability to include yokes produced under a PMA whose design 
approval was based on identicality with the affected Bell yoke. The 
NPRM also proposed giving operators credit for the accumulated 
operating time on certain yokes covered by the superseded ADs.
    The proposed requirements of this AD were intended to prevent 
cracking of a yoke, failure of the yoke, and subsequent loss of control 
of the helicopter.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (76 FR 67628, 
November 2, 2011).

Related Service Information

    Bell issued Alert Service Bulletins (ASBs) Nos. 204-92-36, 205-92-
51, and 212-92-80, all dated October 23, 1992. These ASBs specify 
replacing yoke P/N 204-011-102 (all dash numbers) by December 31, 1993, 
with yoke P/N 212-011-102-105 or -109, depending on the helicopter 
configuration. The replacement yokes are made from stainless steel and 
have improved design characteristics that address the corrosion 
problems and are not subject to any heavy lift cycle counting required 
for previous yokes installed on the Model 205B and 212 helicopters.

FAA's Determination

    We have reviewed the relevant information and determined that an 
unsafe condition is likely to exist or develop on other products of 
these same type designs and that air safety and the public interest 
require adopting the AD requirements as proposed except for minor 
editorial changes and a change to correct one instance of the word 
``Unfactored'' to the word ``Factored.'' In addition, the notes were 
removed to prevent any misconception that they were mandatory 
procedures. These minor editorial changes are consistent with the 
intent of the proposals in the

[[Page 4760]]

NPRM and will not increase the economic burden on any operator nor 
increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 15 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. Reviewing the helicopter records and 
determining the total factored hours TIS will require about 3 work 
hours at an average labor rate of $85 per hour, for a total cost of 
$255 per helicopter and a total cost to the U.S. operator fleet of 
$3,825. Removing the yoke from the helicopter and performing a visual 
inspection and MPI will require about 35 work hours at an average labor 
rate of $85 per work hour, for a total cost of $2,975 per helicopter 
and a total cost to the U.S. operator fleet of $44,625 per inspection 
cycle.
    To replace a yoke will require about 32 work hours at an average 
labor rate of $85 per hour for labor costs of $2,720 per helicopter, 
and required parts will cost $40,157 for a total cost per helicopter of 
$42,877 and a total cost to the U.S. operator fleet of $643,155.

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 above, I certify that this AD:
    (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);
    (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 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 Amendments 39-8507 (58 FR 
13700, March 15, 1993); 39-4208 (46 FR 45595, September 14, 1981); 39-
4207 (46 FR 45595, September 14, 1981); 39-3662 (45 FR 6922, January 
31, 1980); 39-3626 (44 FR 70123, December 6, 1979); and 39-3572 (44 FR 
55556, September 27, 1979); and by adding a new airworthiness directive 
(AD) to read as follows:

2012-17-08 Bell Helicopter Textron, Inc. (Bell): Amendment 39-17171; 
Docket No. FAA-2011-1188; Directorate Identifier 2008-SW-46-AD.

(a) Applicability

    This AD applies to Model 204B, 205A, 205A-1, 205B, and 212 
helicopters, with a main rotor yoke (yoke), part number (P/N) AAI-
4011-102 (all dash numbers), ASI-4011-102 (all dash numbers), or 
204-011-102 (all dash numbers), installed, certificated in any 
category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a yoke. This 
condition could result in failure of a yoke, and subsequent loss of 
control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 93-05-01, Amendment 39-8507 (58 FR 13700, 
March 15, 1993); AD 81-19-02, Amendment 39-4208 (46 FR 45595, 
September 14, 1981; AD 81-19-01, Amendment 39-4207 (46 FR 45595, 
September 14, 1981); and AD 79-20-05, Amendments 39-3662 (45 FR 
6922, January 31, 1980), 39-3626 (44 FR 70123, December 6, 1979), 
and 39-3572 (44 FR 55556, September 27, 1979).

(d) Effective Date

    This AD becomes effective February 27, 2013.

(e) 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.

(f) Required Actions

    (1) For helicopters with yoke, P/N AAI-4011-102 (all dash 
numbers) and ASI-4011-102 (all dash numbers), installed, within 100 
hours time-in-service (TIS):
    (i) Create a component history card or equivalent record for 
each yoke.
    (ii) Determine the model for each helicopter on which the yoke 
has been installed from the time the yoke had zero hours TIS.
    (iii) In accordance with the rate per hour categories shown in 
Table 1 to paragraph (f) of this AD, categorize the accumulated 
``Factored Hours TIS'' on each yoke by determining the types of 
operation AND the rate per hour of external load lifts for each hour 
TIS accumulated on each yoke. One external load lift occurs each 
time the helicopter picks up an external load and drops it off. For 
determining the proper rate per hour category for external load 
operations, any external load lift in which the helicopter achieves 
a vertical altitude difference of greater than 200 feet indicated 
altitude between the pickup and drop-off point counts as two 
external load lifts.

[[Page 4761]]

                                                 Table 1 to Paragraph (f)--Factored Hours TIS for a Yoke
                           [Number of unfactored hours TIS and factored hours TIS are examples for illustration purposes only]
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                                          Factored hours
                                                                                                                                            TIS on yoke
                                                                        Rate per hour of external load     Unfactored       Hours TIS       (unfactored
            Helicopter model                   Types of operation             lifts and takeoffs            hours TIS         factor        hours TIS x
                                                                                                                                             hours TIS
                                                                                                                                              factor)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Yokes installed on any Model 204B, 205A,  All Operations.............  All.............................             120              1               120
 or 205A-1 helicopter.
Yokes installed on any Model 205B or 212  External Load Operations...  1 to 5..........................             105              1               105
 helicopter.
                                                                       5.1 to 8........................                              1.5  ..............
                                                                       8.1 to 12.......................                              2    ..............
                                                                       12.1 to 18......................                              3    ..............
                                                                       18.1 to 32......................             170              5               850
                                                                       32.1 to 48......................                              7    ..............
                                                                       more than 48....................                              9    ..............
                                                                       Unknown.........................              50              7               350
                                          Internal Load Operations...  All Takeoffs....................           2,025              1             2,025
--------------------------------------------------------------------------------------------------------------------------------------------------------
Total Factored Hours TIS on Yoke (Summation of the Factored Hours TIS)                                                                             3,450
--------------------------------------------------------------------------------------------------------------------------------------------------------

     (iv) By reference to Table 1 to paragraph (f) of this AD, enter 
the ``Unfactored Hours TIS'' for each category as determined by 
paragraph (f)(1)(iii) of this AD. Calculate the ``Factored Hours 
TIS'' by multiplying the ``Unfactored Hours TIS'' by the ``Hours TIS 
Factor.'' Determine the accumulated ``Total Factored Hours TIS'' on 
each yoke by adding the factored hours TIS for each type of 
operation and helicopter model. Tracking the Total Factored Hours 
TIS is only for establishing a retirement life and not for tracking 
inspection intervals.
    (v) Record the accumulated Total Factored Hours TIS on the 
component history card or equivalent record for each yoke.
    (vi) Continue to factor the hours TIS for each yoke by following 
paragraph (f)(1)(ii) through (f)(1)(iv) of this AD, and record the 
additional factored hours TIS on the component history card or 
equivalent record.
    (2) For helicopters with yoke, P/N 204-011-102 (all dash 
numbers), installed, before further flight:
    (i) For hours TIS accumulated before the effective date of this 
AD, calculate and record the Total Factored Hours TIS as follows:
    (A) For the Model 212 helicopters, 1 hour TIS in which passenger 
or internal cargo was carried equals 1 factored hour TIS; 1 hour TIS 
where more than 4 external load lifts occurred equals 5 factored 
hours TIS.
    (B) For the Model 204 and 205 series helicopters, 1 hour TIS 
equals 1 factored hour TIS.
    (ii) For hours TIS accumulated after the effective date of this 
AD, calculate and record the factored hours TIS on the yoke in 
accordance with the requirements of paragraphs (f)(1)(i) thorough 
(f)(1)(vi) of this AD.
    (3) Revise the Airworthiness Limitations section of the 
applicable maintenance manuals or the Instructions for Continued 
Airworthiness (ICAs) by establishing a new retirement life of 3,600 
Total Factored Hours TIS for each yoke, P/N AAI-4011-102 (all dash 
numbers), ASI-4011-102 (all dash numbers), or 204-011-102 (all dash 
numbers), by making pen and ink changes or inserting a copy of this 
AD into the Airworthiness Limitations section of the maintenance 
manual or ICAs.
    (4) Record a life limit of 3,600 Total Factored Hours TIS for 
each yoke, P/N AAI-4011-102 (all dash numbers), ASI-4011-102 (all 
dash numbers), or 204-011-102 (all dash numbers), on the component 
history card or equivalent record.
    (5) Within 100 hours TIS or 600 hours TIS since the last 
magnetic particle inspection (MPI) of the yoke, whichever occurs 
later, and thereafter at intervals not to exceed 600 hours TIS, for 
any yoke installed on any Model 205B or 212 helicopter:
    (i) Remove the yoke from the main rotor hub assembly (hub). 
Using a 5-power or higher magnifying glass, visually inspect each 
pillow block bushing hole, spindle radius, and center section web 
for any corrosion or mechanical damage.
    (ii) Perform an MPI of each yoke for a crack.
    (6) Within 100 hours TIS or 2,400 hours TIS since the last MPI 
of the yoke, whichever occurs later, and thereafter at intervals not 
to exceed 2,400 hours TIS, for any yoke installed on any Model 204B, 
205A, or 205A-1 helicopter:
    (i) Remove the yoke from the hub. Using a 5-power or higher 
magnifying glass, visually inspect each pillow block bushing hole, 
spindle radius, and center section web for any corrosion or 
mechanical damage.
    (ii) Perform an MPI of each yoke for a crack.
    (7) Before further flight, replace each yoke with an airworthy 
yoke if:
    (i) The yoke has 3,600 or more Total Factored Hours TIS; or
    (ii) The Total Factored Hours TIS for the yoke is unknown and 
cannot be determined; or
    (iii) The yoke has any corrosion or mechanical damage that 
exceeds any of the maximum repair damage limits; or
    (iv) The yoke has a crack.

(g) Special Flight Permits

    Special flight permits may only be issued under 14 CFR 21.197 
and 21.199 for the purpose of operating the helicopter to a location 
where the MPI requirements of paragraphs (f)(5) or (f)(6) of this AD 
can be performed.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Michael Kohner, 
Aviation Safety Engineer, Rotorcraft Certification Office, 
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 
76137; telephone (817) 222-5170; email 7-avs-asw-170@faa.gov.
    (2) For operations conducted under a 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.

(i) Additional Information

    Bell Alert Service Bulletin Nos. 204-92-36, 205-92-51, and 212-
92-80, all dated October 23, 1992, which are not incorporated by 
reference, contain additional information about the subject of this 
AD. For service information identified in this 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 this service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6220: Main Rotor 
Head.

[[Page 4762]]

    Issued in Fort Worth, Texas, on December 21, 2012.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-00985 Filed 1-22-13; 8:45 am]
BILLING CODE 4910-13-P