[Federal Register: March 13, 2007 (Volume 72, Number 48)]
[Proposed Rules]
[Page 11295-11297]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13mr07-9]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27496; Directorate Identifier 2005-SW-37-AD]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron, Inc. Model
205A, 205A-1, 205B, 212, 412, 412CF, and 412EP Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes superseding an existing airworthiness
directive (AD) for the specified Bell Helicopter Textron, Inc. (Bell)
helicopters. That AD currently requires inspecting each affected tail
rotor blade (blade) forward tip weight retention block (tip block) and
the aft tip closure (tip closure) for adhesive bond voids, and removing
any blade with an excessive void from service. That AD also requires
modifying certain blades by installing shear pins and tip closure
rivets. This action would contain the same requirements but would
expand the applicability to include other part and serial-numbered
blades. This AD would also clarify the requirement to re-identify the
modified blade by adding ``FM'' after the part number and would require
dynamically balancing the tail rotor. The existing AD was prompted by
five occurrences of missing tip blocks or tip closures resulting in
minor to substantial damage. This proposal was prompted by the
determination that the AD should apply to other affected part and
serial-numbered blades. The actions specified by this proposed AD are
intended to prevent loss of a tip block or tip closure, loss of a
blade, and subsequent loss of control of the helicopter.
DATES: Comments must be received on or before May 14, 2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD:
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically;
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically;
Mail: Docket Management Facility; U.S. Department of
Transportation, 400
[[Page 11296]]
Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC
20590;
Fax: 202-493-2251; or
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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://dms.dot.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-2007-
27496, Directorate Identifier 2005-SW-37-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://dms.dot.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 our 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) or you may visit http://dms.dot.gov.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Management
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of
Transportation NASSIF Building in Room PL-401 at 400 Seventh Street,
SW., Washington, DC. Comments will be available in the AD docket
shortly after the DMS receives them.
Discussion
On April 22, 2002, we issued AD 2002-09-04, Amendment 39-12737 (67
FR 22349, May 3, 2002), to require inspecting the tip block and the tip
closure for adhesive bonding voids, and removing any blade with an
excessive void from service. The AD also required modifying certain
blades by installing shear pins and tip closure rivets in the tip area
of the affected blades. That action was prompted by five occurrences of
missing tip blocks or tip closures resulting in minor to substantial
damage. The requirements of that AD are intended to prevent loss of a
tip block or tip closure, loss of a blade, and subsequent loss of
control of the helicopter.
Since issuing that AD, Bell has issued further revisions to Alert
Service Bulletin (ASB) Nos. 205-00-80, 205B-00-34, 212-00-111, 412-00-
106, and 412CF-00-13, Revision A, dated December 20, 2000. The
revisions add blades with a serial number (S/N) A or AFS-11530 to
13594, 13603 to 13618, and changed the ``effectivity'' of the blades.
The latest revision, Revision D, dated March 18, 2005, provides an
alternate fastener for the blade tip closure rivets installation. The
revised ASB also states that blades with S/N A or AFS-11926, 13351,
13367, 13393, 13400, 13402, 13515, 13540, 13568, 13595 to 13602, and
13619 and subsequent will have the intent of the ASBs accomplished
before delivery.
The previously described unsafe condition is likely to exist or
develop on other helicopters of these same type designs. Therefore, the
proposed AD would supersede AD 2002-09-04 to expand the applicability
for the blade part and serial number. The proposed AD would also
clarify the requirement to re-identify the modified blade by adding
``FM'' after the part number and would also require dynamically
balancing the tail rotor. Because blades with a S/N with a prefix of
``A'' or ``AFS'' and a number 11926, 13351, 13367, 13393, 13400, 13402,
13515, 13540, 13568, 13595 to 13602, and 13619 and subsequent will have
the modification required by this AD accomplished before delivery, we
would exclude them from the applicability of this AD.
We estimate that this proposed AD would affect 281 helicopters of
U.S. registry. The proposed actions would take about 3 work hours per
helicopter to inspect certain blades, install the shear pins and tip
closure rivets, re-identify the modified blades, and dynamically
balance the blade assembly at an average labor rate of $80 per work
hour. Required supplies would cost about $35 per helicopter. Based on
these figures, we estimate the total cost impact of the AD on U.S.
operators to be $77,275.
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;
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. See the DMS 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.
[[Page 11297]]
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 removing Amendment 39-12737 (67 FR
22349, May 3, 2002), and by adding a new airworthiness directive (AD),
to read as follows:
Bell Helicopter Textron, Inc.: Docket No. FAA-2007-27496;
Directorate Identifier 2005-SW-37-AD. Supersedes AD 2002-09-04,
Amendment 39-12737, Docket No. 2001-SW-37-AD.
Applicability
Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters
with a tail rotor blade (blade), part number 212-010-750-009 through
-129, all serial numbers except serial numbers with a prefix of
``A'' or ``AFS'' and the number 11926, 13351, 13367, 13393, 13400,
13402, 13515, 13540, 13568, 13595 through 13602, 13619, and
subsequent assigned numbers, installed, certificated in any
category.
Compliance
Within 100 hours time-in-service, unless accomplished
previously.
To prevent loss of the forward tip weight retention block (tip
block) or aft tip closure (tip closure), loss of the blade, and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Inspect the tip block and tip closure for voids. Remove from
service any blade with a void in excess of that allowed by the
Component Repair and Overhaul Manual limitations.
(b) Inspect the tip block attachment countersink screws in four
locations to determine if the head of each countersunk screw is
flush with the surface of the abrasion strip. The locations of these
four screws are depicted on Figure 1 of Bell Helicopter Textron,
Inc. Alert Service Bulletins 205-00-80, 205B-00-34, 212-00-111, 412-
00-106, and 412CF-00-13, all Revision D, all dated March 18, 2005
(ASB). If any of these screws are set below the surface of the
abrasion strip or are covered with filler material, install shear
pins by following the Accomplishment Instructions, Part A, Shear Pin
Installation paragraphs, of the ASB appropriate for your model
helicopter.
(c) Install the aft tip closure rivets, re-identify the modified
blade by adding an ``FM,'' and dynamically balance the tail rotor
hub assembly by following the Accomplishment Instructions, Part B,
Aft Tip Closure Rivet Installation paragraphs, of the ASB
appropriate for your model helicopter.
(d) 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, Rotorcraft
Directorate, 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 February 28, 2007.
S. Frances Cox,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-4525 Filed 3-12-07; 8:45 am]
BILLING CODE 4910-13-P