[Federal Register: October 26, 2007 (Volume 72, Number 207)]
[Rules and Regulations]
[Page 60760-60762]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26oc07-3]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27496; Directorate Identifier 2005-SW-37-AD;
Amendment 39-15238; AD 2007-22-02]
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: Final Rule.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes 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 amendment contains the same requirements but expands the
applicability to include other part and serial-numbered blades. This AD
also clarifies the requirement to re-identify the modified blade by
adding ``FM'' after the part number and also requires 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 amendment was prompted by the determination
that the AD should apply to other affected part and serial-numbered
blades. The actions specified by this 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: Effective November 30, 2007.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 30, 2007.
ADDRESSES: You may get the service information identified in this AD
from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas
76101, telephone (817) 280-3391, fax (817) 280-6466.
Examining the Docket: You may examine the AD docket on the Internet
at http://www.regulations.gov; or in person at the Docket Management
Facility between 9 a.m. and 5 p.m. Monday through Friday, except
Federal holidays. The AD docket contains this AD, the regulatory
evaluation, any comments received, and other information. The address
for the Docket Office (telephone 800-647-5527) is the Document
Management Facility, U.S. Department of Transportation, Docket
Operations, 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, FAA, Rotorcraft Directorate, Rotorcraft Certification Office,
Fort Worth, Texas 76193-0170, telephone (817) 222-5447, fax (817) 222-
5783.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by
superseding AD 2002-09-04, Amendment 30-12737 (67 FR 22349, May 3,
2002), for the specified Bell model helicopters was published in the
Federal Register on March 13, 2007 (72 FR 11295). The action proposed:
retaining requirements to inspect the tip block and the tip closure for
adhesive bonding voids and to remove any blade with an excessive void
from service; retaining requirements to modify certain blades by
installing shear pins and tip closure rivets in the tip area of the
affected blades; expanding the applicability to include more blades and
clarifying other requirements.
Since issuing AD 2002-09-04, Bell issued further revisions to Alert
Service Bullet (ASB) Nos. 205-00-80, 205B-00-
[[Page 60761]]
34, 212-00-111, 412-00-106, and 412CR-00-13, Revision A, dated December
20, 2000. The revisions add blades with a serial number (S/N) prefix of
``A'' or ``AFS'' and number of 11530 to 13594, 13603 to 13618, and also
change the ``effectivity'' of the blades. The latest revisions,
Revisions D, all dated March 18, 2005, provide an alternative fastener
for the blade tip closure rivets installation. The revised ASBs also
state that blades with S/N A or AFS-11926, 13351, 13367, 13393, 13400,
13402, 13515, 13540, 13568, 13595 to 13602, 13619, and subsequent will
be modified before delivery.
The previously described unsafe condition is likely to exist or
develop on other helicopters of these same type designs. Therefore,
this AD supersedes AD 2002-09-04 to expand the applicability for the
blade part and serial number. This AD also clarifies the requirement to
re-identify the modified blade by adding ``FM'' after the part number
and also requires dynamically balancing the tail rotor. Because blades,
S/N with a prefix of ``A'' or ``AFS'' and a number 11926, 13351, 13367,
13393, 13400, 13402, 13515, 13540, 13568, 13595 to 13602, 13619, and
subsequent, will be modified before delivery, we are excluding them
from the applicability of this AD.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
The FAA estimates that this AD will affect 281 helicopters of U.S.
registry. The required actions will take about 3 work hours per
helicopters to inspect certain blades, install the shear pins and tip
closure rivets, reidentify the modified blades, and dynamically balance
the blade assembly at an average labor rate of $80 per work hour.
Required supplies will 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 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 reason discussed above, I certify that the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12833;
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 an economic evaluation of the estimated costs to comply
with this AD. See the AD docket to examine the 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, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39-12737 (67 FR
22349, May 3, 2002), and by adding a new airworthiness directive (AD),
Amendment 39-15238, to read as follows:
2007-22-02 Bell Helicopter Textron, Inc.: Amendment 39-15238. 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
hum 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.
(e) Inspecting certain screws to determine if they are flush
with the surface of the abrasion strip, modifying blades by
installing shear pins or aft tip closure rivets as necessary, and
re-identifying the modified blade shall be done by following 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. The Director of the Federal Register approved
this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be
[[Page 60762]]
obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Fort
Worth, Texas 76101, telephone (817) 280-3391, fax (817) 280-6466.
Copies may be inspected at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
(f) This amendment becomes effective November 30, 2007.
Issued in Fort Worth, Texas, on October 10, 2007.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 07-5186 Filed 10-25-07; 8:45 am]
BILLING CODE 4910-13-M