[Federal Register Volume 72, Number 207 (Friday, October 26, 2007)]
[Rules and Regulations]
[Pages 60760-60762]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 07-5186]


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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; 
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.

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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