[Federal Register: February 17, 2005 (Volume 70, Number 32)]
[Rules and Regulations]
[Page 8021-8025]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17fe05-1]
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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
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
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[[Page 8021]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20107; Directorate Identifier 2005-SW-02-AD;
Amendment 39-13981; AD 2005-04-09]
RIN 2120-AA64
Airworthiness Directives; Bell Helicopter Textron Canada Model
222, 222B, 222U, 230, and 430 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD) for the specified Bell Helicopter Textron Canada (BHTC) model
helicopters that currently requires certain checks and inspections of
the tail rotor blades. If a crack is found, the existing AD requires
replacing the tail rotor blade (blade) with an airworthy blade before
further flight. This amendment requires the same checks and inspections
as the existing AD, but expands the applicability with the addition of
two BHTC Model 430 helicopter serial numbers. This amendment is
prompted by the manufacturer issuing revised service information that
includes the additional two serial numbers. The actions specified by
this AD are intended to detect a crack in the blade, and to prevent
loss of a blade and subsequent loss of control of the helicopter.
DATES: Effective March 4, 2005.
Comments for inclusion in the Rules Docket must be received on or
before April 18, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this 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 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 AD from Bell
Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272.
You may examine this information 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
.
Examining the Docket: You may examine the docket that contains the AD,
any comments, and other information on the Internet at http://dms.dot.gov
, or in person at the Docket Management System (DMS) Docket
Offices between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5227) is
located on the plaza level of the Department of Transportation Nassif
Building at the street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after the DMS
receives them.
FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group,
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.
SUPPLEMENTARY INFORMATION: On December 23, 2004, the FAA issued AD
2004-26-11, Amendment 39-13923 (70 FR 7; January 3, 2005), to require
certain checks and inspections of the blades. If a crack is found, that
AD requires replacing the blade with an airworthy blade before further
flight. That action was prompted by three reports of cracked blades
that were found during scheduled inspections. That condition, if not
corrected, could result in loss of a blade and subsequent loss of
control of the helicopter.
Since issuing that AD, the alert service bulletin (ASB) that is
applicable to BHTC Model 430 helicopters has been revised by the
manufacturer to include two additional helicopter serial numbers.
Further, we discovered two typographical errors in the AD--the word
``Canada'' is inadvertently omitted from the manufacturer's name in the
Summary section, and in Note 1 of the AD, the number for the Model 430
helicopter ASB is incorrectly stated as 430-04-32 instead of 430-04-
31--as well as some minor editorial errors, which have been corrected
in this AD.
Transport Canada, the airworthiness authority for Canada, notified
the FAA that an unsafe condition may exist on the specified BHTC model
helicopters. Transport Canada advises of the discovery of cracked
blades during scheduled inspections on three occasions. Two cracks
originated from the outboard feathering bearing bore underneath the
flanged sleeves. The third crack started from the inboard feathering
bearing bore. Investigation found that the cracks originated from
either a machining burr or a corrosion site in the bearing bore
underneath the flanged sleeves.
BHTC has issued ASB No. 222-04-100 for Model 222 and 222B
helicopters; ASB No. 222U-04-71 for Model 222U helicopters; and ASB No.
230-04-31 for Model 230 helicopters, all dated August 27, 2004; and,
ASB No. 430-04-31, Revision A, dated November 29, 2004, for Model 430
helicopters. The ASBs specify a visual inspection of the blade root end
around the feather bearings for a crack, not later than at the next
scheduled inspection, and thereafter at intervals not to exceed 3
flight hours. Further, they describe a visual inspection for a crack,
to include removing the blade from the helicopter, within 50 flight
hours, and thereafter at intervals not to exceed 50 flight hours.
Transport Canada classified these ASBs as mandatory and issued AD CF-
2004-21R1, dated December 9, 2004, to ensure the continued
airworthiness of these helicopters in Canada. This AD differs from
those ASBs in that it requires an initial visual check, which may be
[[Page 8022]]
performed by a pilot, within 3 hours time-in-service (TIS) rather than
a visual inspection not later than at the next scheduled inspection and
every 3 flight hours maximum thereafter as stated in the ASBs.
These helicopter models are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, Transport Canada has kept the FAA
informed of the situation described above. The FAA has examined the
findings of Transport Canada, reviewed all available information, and
determined that AD action is necessary for products of these type
designs that are certificated for operation in the United States.
This previously described unsafe condition is likely to exist or
develop on other helicopters of the same type design. Therefore, this
AD supersedes AD 2004-26-11 to require the following:
Within 3 hours TIS, and thereafter at intervals not to
exceed 3 hours TIS, clean and visually check both sides of each blade
for a crack in the area around the tail rotor feathering bearing. An
owner/operator (pilot) may perform this check. Pilots may perform the
checks required by paragraph (a) of this AD because they require no
tools, can be done by observation, and can be done equally well by a
pilot or a mechanic. However, the pilot must enter compliance with
these requirements into the helicopter maintenance records by following
14 CFR 43.11 and 91.417(a)(2)(v).
Within 50 hours TIS, and thereafter at intervals not to
exceed 50 hours TIS, clean and inspect both sides of each blade for a
crack using a 10X or higher magnifying glass.
If a crack is found in the blade paint during a visual
check or inspection, further inspect the blade as follows, before
further flight:
Remove the blade. Remove the paint to the bare metal in
the area of the suspected crack by using plastic metal blasting (PMB)
or a nylon web abrasive pad and abrading the blade surface in a span-
wise direction only.
Using a 10X or higher power magnifying glass, inspect the
blade for a crack.
If a crack is found, replace the blade with an airworthy
blade before further flight.
If no crack is found in the blade surface, refinish the
blade by applying one coat of epoxy polyamide primer, MIL-P-23377 or
MIL-P-85582, so that the primer overlaps the existing coats just beyond
the abraded area. Let the area dry for 30 minutes to 1 hour. Then,
apply one sealer coat of polyurethane, MILC85285 TYI CL2, color number
27925 (semi-gloss white), per Fed. Std. 595, and reinstall the blade.
This AD is an interim action, pending release of additional service
information from the manufacturer concerning instructions for
inspecting and reworking the affected blades. We expect that service
information to eliminate the recurring inspections required by this AD.
The short compliance time involved is required because the
previously described critical unsafe condition can adversely affect the
controllability and structural integrity of the helicopter. Therefore,
checking the blade for a crack within 3 hours TIS, and thereafter at
intervals not to exceed 3 hours TIS, is required, and this AD must be
issued immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
We estimate that this AD will affect 156 helicopters and will
require:
0.25 work hour for a pilot check, and 2 work hours for a
maintenance inspection, at an average labor rate of $65 per work hour;
and
Parts, which will cost an estimated $13,410 per
helicopter.
Based on these figures, the estimated total cost impact of the AD
on U.S. operators is $2,842,320 per year, assuming each helicopter will
require 200 pilot checks, 12 maintenance inspections, and one blade
replacement per year.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any written data,
views, or arguments regarding this AD. Send or deliver your comments to
an address listed under ADDRESSES. Include ``Docket No. FAA-2005-20107;
Directorate Identifier 2005-SW-02-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the 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 AD. 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 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
.
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 reasons discussed above, I certify that the 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 an economic evaluation of the estimated costs to comply
with this AD. See the DMS 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, Safety.
[[Page 8023]]
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 39-13923 (70 FR 7,
January 3, 2005), and by adding a new airworthiness directive (AD),
Amendment 39-13981, to read as follows:
2005-04-09 Bell Helicopter Textron Canada: Amendment 39-13981.
Docket No. FAA-2005-20107; Directorate Identifier 2005-SW-02-AD.
Supersedes AD 2004-26-11, Amendment 39-13923, Docket No. FAA-2004-
19969, Directorate Identifier 2004-SW-43-AD.
Applicability: The following helicopter models, identified by
serial number, with one of the following part numbered tail rotor
blades installed, certificated in any category.
----------------------------------------------------------------------------------------------------------------
Model Serial No. Tail rotor blade (blade) part no.
----------------------------------------------------------------------------------------------------------------
222............................... 47006 through 47089. 222-016-001-123, -127, -131, and -135.
222B.............................. 47131 through 47156. 222-016-001-123, -127, -131, and -135.
222U.............................. 47501 through 47574. 222-016-001-123, and -131.
230............................... 23001 through 23038. 222-016-001-123, and -131.
430............................... 49001 through 49107. 222-016-001-123, and -131.
----------------------------------------------------------------------------------------------------------------
Compliance: Required as indicated.
To detect a crack in the blade and to prevent loss of the blade
and subsequent loss of control of the helicopter, accomplish the
following:
(a) Within 3 hours time-in-service (TIS), and thereafter at
intervals not to exceed 3 hours TIS, clean and visually check both
sides of each blade for a crack in the paint in the areas shown in
Figure 1 of this AD. An owner/operator (pilot), holding at least a
private pilot certificate, may perform this visual check and must
enter compliance with this paragraph into the helicopter maintenance
records by following 14 CFR 43.11 and 91.417(a)(2)(v).
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[[Page 8024]]
[GRAPHIC] [TIFF OMITTED] TR17FE05.002
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Note 1: Bell Helicopter Textron Alert Service Bulletin (ASB) No.
222-04-100, No. 222U-04-71, and No. 230-04-31, all dated August 27,
2004, and ASB No. 430-04-31, Revision A, dated November 29, 2004,
pertain to the subject of this AD.
(b) If the visual check required by paragraph (a) reveals a
crack in the paint, before further flight, remove the blade and
follow the requirements in paragraphs (c)(2) through (c)(3)(ii) of
this AD.
(c) Within the next 50 hours TIS, unless accomplished
previously, and thereafter at intervals not to exceed 50 hours TIS,
clean the blade by wiping down both surfaces of each blade in the
inspection area depicted in Figure 1 of this AD using aliphatic
naphtha (C-305) or detergent (C-318) or an equivalent. Using a 10X
or higher power magnifying glass, visually inspect both sides of the
blade in the areas depicted in Figure 1 of this AD.
(1) If a crack is found, even if only in the paint, before
further flight, remove the blade from the helicopter and proceed
with the following:
(2) Remove the paint on the blade down to the bare metal in the
area of the suspected crack by using plastic metal blasting (PMB) or
a nylon web abrasive pad. Abrade the blade surface in a span-wise
direction only.
Note 2: PMB may cause damage to helicopter parts if untrained
personnel perform the paint removal. BHT-ALL-SPM, chapter 3,
paragraph 3-24, pertains to the subject of this AD.
(3) Using a 10X or higher power magnifying glass, inspect the
blade for a crack.
[[Page 8025]]
(i) If a crack is found, replace the blade with an airworthy
blade before further flight.
(ii) If no crack is found in the blade surface, refinish the
blade by applying one coat of epoxy polyamide primer, MIL-P-23377 or
MIL-P-85582, so that the primer overlaps the existing coats just
beyond the abraded area. Let the area dry for 30 minutes to 1 hour.
Then, apply one sealer coat of polyurethane, MILC85285 TYI CL2,
color number 27925 (semi-gloss white), per Fed. Std. 595. Reinstall
the blade.
Note 3: BHT-ALL-SPM, chapter 4, pertains to painting the blade.
(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 Safety Management Group, FAA, for information about
previously approved alternative methods of compliance.
(e) Special flight permits may be issued by following 14 CFR
21.197 and 21.199 to operate the helicopter to a location where the
requirements of this AD can be accomplished provided you do not find
a crack in the blade paint during a check or inspection.
(f) This amendment becomes effective March 4, 2005.
Note 4: The subject of this AD is addressed in Transport Canada
(Canada) Airworthiness Directive CF-2004-21R1, dated December 9,
2004.
Issued in Fort Worth, Texas, on February 10, 2005.
Kim Smith,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-3049 Filed 2-16-05; 8:45 am]
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