[Federal Register Volume 78, Number 15 (Wednesday, January 23, 2013)]
[Rules and Regulations]
[Pages 4759-4762]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-00985]
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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
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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.
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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 [email protected].
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)
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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
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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 [email protected].
(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