[Federal Register Volume 73, Number 50 (Thursday, March 13, 2008)]
[Proposed Rules]
[Pages 13513-13515]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-5060]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0288; Directorate Identifier 2006-SW-25-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron, Inc. Model 
214B and B-1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Bell Helicopter Textron, Inc. (BHTI) Model 214B and B-1 
helicopters. The AD would require creating a component history card or 
equivalent for each pylon support spindle assembly (spindle), and 
inspecting certain spindles for any corrosion, or a nick, scratch, 
dent, or crack, and replacing any unairworthy spindle before further 
flight. This proposal is prompted by three in-flight failures of 
spindles that resulted in forced landings. The actions specified by the 
proposed AD are intended to detect damage in the radii or cracking of a 
spindle, and to prevent failure of a spindle and subsequent loss of 
control of the helicopter.

DATES: Comments must be received on or before May 12, 2008.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:

[[Page 13514]]

     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590;
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
     Fax: 202-493-2251.
    You may get the service information identified in this proposed AD 
from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 
76101, telephone (817) 280-3391, fax (817) 280-6466.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at http://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
5783.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2008-0288, 
Directorate Identifier 2006-SW-25-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed rulemaking. Using the 
search function of the docket Web site, you can find and read the 
comments to any of our dockets, including the name of the individual 
who sent or signed the comment. You may review the DOT's complete 
Privacy Act Statement in the Federal Register published on April 11, 
2000 (65 FR 19477-78).

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Operations 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Operations office (telephone (800) 647-5527) is 
located in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

Discussion

    This document proposes adopting a new AD for BHTI Model 214B and B-
1 helicopters. The AD would require, within 50 hours time-in-service 
(TIS), creating a component history card or equivalent record for each 
spindle, and begin recording the spindle's TIS and number of take-offs 
and external load lifts accomplished with the spindle installed. It 
would also require a one-time visual inspection of the outer radius of 
the spindle for any corrosion or a nick, scratch, or dent, using a 3x-
power or higher magnifying glass, and a one-time magnetic particle 
inspection of the spindles for a crack. The inspections would be 
required within 100 hours TIS, or 325 hours TIS since the last overhaul 
of the transmission assembly, whichever occurs later, for spindles with 
5,000 or more hours TIS, or spindles for which the total number of 
hours TIS is unknown and were installed before the last overhaul of the 
transmission assembly. For spindles having 5,000 or more hours TIS, or 
spindles for which the total number of hours TIS is unknown, that were 
installed after the last overhaul of the transmission assembly, or the 
installation history is unknown, the inspections would be required 
within 100 hours TIS. The proposed AD would also require, before 
further flight, replacing any spindle on which any corrosion or a crack 
is discovered, and replacing any spindle that has a nick, scratch, or 
dent, or repairing the spindle if the damage is within the repair 
limits that are stated in the applicable component repair and overhaul 
manual. This proposal is prompted by three in-flight failures of the 
spindle, part number 214-030-606-005, which resulted in forced landings 
and one serious injury. All three helicopters were involved in logging 
operations, which put more torque cycles on the main rotor and 
transmission systems. The failures occurred at 694, 810, and 1,928 
hours TIS since the last overhaul of the transmission assembly on 
helicopters having a total TIS of 3,500 to 17,000 hours. Currently, the 
spindles do not have a retirement life on either the Model 214B or 
214B-1 helicopters, and the number of hours TIS for the spindles is not 
required to be tracked on a component history card or equivalent 
record. The current inspections specified in the maintenance manuals 
are a magnetic particle inspection at each 2,500 hours TIS transmission 
overhaul, and a visual inspection for mechanical or corrosion damage, 
using a 3x-power magnifying glass, at each main rotor tension-torsion 
strap change. A magnetic particle inspection is also required following 
the occurrence of a sudden stoppage of the main rotor system. The 
actions specified by the proposed AD are intended to detect damage in 
the radii or cracking of a spindle, and to prevent failure of a spindle 
and subsequent loss of control of the helicopter. The actions of this 
proposed AD are intended as interim actions until a retirement life for 
these spindles can be developed and new replacement spindles become 
available.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, the proposed AD would 
require creating a component history card or equivalent for each 
spindle, inspecting certain spindles for any corrosion, or a nick, 
scratch, dent, or crack, and replacing any unairworthy spindle before 
further flight.
    We estimate that this proposed AD would affect 10 helicopters of 
U.S. registry, and the proposed actions would take approximately:
     15 work hours to remove and replace a set of spindles for 
inspecting;
     2 work hours to conduct a magnetic particle inspection; 
and
     15 work hours to replace a set of spindles at an average 
labor rate of $80 per work hour. Required parts would cost 
approximately $10,735 for a set of spindles. Based on these figures, 
the total cost impact of the proposed AD on U.S. operators would be 
$25,535, assuming the inspections are performed once for each 
helicopter and one set of spindles is replaced.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, 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 above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;

[[Page 13515]]

    2. Is not a ``significant rule'' under the 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.
    We prepared a draft economic evaluation of the estimated costs to 
comply with this proposed AD. Go to the government-wide rulemaking Web 
site at: http://www.regulations.gov to examine the draft economic 
evaluation.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Bell Helicopter Textron, Inc.: Docket No. FAA-2008-0288; Directorate 
Identifier 2006-SW-25-AD.

Applicability

    Model 214B and B-1 helicopters, with pylon support spindle 
assembly (spindle), part number 214-030-606-005, installed, 
certificated in any category.

Compliance

    Required as indicated, unless accomplished previously.
    To detect damage in the radii or cracking of a spindle, and to 
prevent failure of a spindle and subsequent loss of control of the 
helicopter, accomplish the following:
    (a) Within 50 hours time-in-service (TIS):
    (1) Create a component history card or equivalent record for 
each spindle, stating the spindle's serial number. Begin recording 
the number of hours TIS, and the number of take-offs and external 
load lifts. An external load lift occurs when a load is picked up at 
one location and is released at another location.
    (2) Review the helicopter records to determine if there has been 
a sudden stoppage of the main rotor system, or any hard landing, on 
a helicopter with any affected spindle installed and record any such 
events on the component history card or equivalent record.
    (b) Record all conditional inspections of each spindle on the 
component history card or equivalent record. A sudden stoppage of 
the main rotor system is defined as any rapid deceleration of the 
drive system, whether caused by seizure within the helicopter 
transmission or by contact of a main rotor blade with the ground, 
water, snow, dense vegetation, or other object of sufficient inertia 
to cause rapid deceleration.
    (c) For each spindle with 5,000 or more hours TIS, or any 
spindle for which the number of hours TIS is unknown, perform the 
inspections in paragraphs (c)(1) and (c)(2) of this AD within the 
hours TIS specified in Table 1 of this AD:

                                 Table 1
------------------------------------------------------------------------
 For spindles, part number 214-030-606-
    005, that were installed on the              Inspect within:
         transmission assembly:
------------------------------------------------------------------------
Before the last overhaul of the          100 hours TIS or 325 hours TIS
 transmission assembly.                   since the last overhaul of the
                                          transmission assembly,
                                          whichever occurs later.
After the last overhaul of the           100 hours TIS.
 transmission assembly or for which the
 installation history is unknown.
------------------------------------------------------------------------

    (1) Visually inspect each outer radius of the spindle for any 
corrosion, or a nick, scratch, or dent, using a 3x-power or higher 
magnifying glass; and
    (2) Conduct a magnetic particle inspection of the spindle for a 
crack.
    (d) Before further flight, if a crack or any corrosion is found, 
replace the spindle with an airworthy spindle.
    (e) Before further flight, replace any spindle that has a nick, 
scratch, or dent with an airworthy spindle, or repair it if it is 
within the repair limits.

    Note 2: The repair limits are specified in the applicable 
component repair and overhaul manual.

    (f) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Rotorcraft Certification Office, FAA, ATTN: 
Michael Kohner, Aviation Safety Engineer, Fort Worth, Texas 76193-
0170, telephone (817) 222-5447, fax (817) 222-5783, for information 
about previously approved alternative methods of compliance.

    Issued in Fort Worth, Texas, on March 3, 2008.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
 [FR Doc. E8-5060 Filed 3-12-08; 8:45 am]
BILLING CODE 4910-13-P