[Federal Register: January 3, 2005 (Volume 70, Number 1)]
[Rules and Regulations]
[Page 7-10]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03ja05-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19969; Directorate Identifier 2004-SW-43-AD;
Amendment 39-13923; AD 2004-26-11]
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 adopts a new airworthiness directive (AD) for
the specified Bell Helicopter Textron (BHTC) model helicopters. This
action requires certain checks and inspections of the tail rotor
blades. If a crack is found, before further flight, this AD requires
replacing the tail rotor blade (blade) with an airworthy blade. This
amendment is prompted by three reports of cracked blades found during
scheduled inspections. The actions specified in this AD are intended to
detect a crack in the blade and prevent loss of a blade and subsequent
loss of control of the helicopter.
DATES: Effective January 18, 2005.
Comments for inclusion in the Rules Docket must be received on or
before March 4, 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.
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 Guidance Group,
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.
SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for the
specified BHTC model helicopters. This action requires certain checks
and inspections of the blades. If a crack is found, before further
flight, this AD requires replacing the blade with an airworthy blade.
This amendment is prompted by three reports of cracked blades found
during scheduled inspections. This condition, if not detected, could
result in loss of a blade and subsequent loss of control of the
helicopter.
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 Alert Service Bulletin (ASB) No. 222-04-100 for
Model 222 and 222B helicopters, No. 222U-04-71 for Model 222U
helicopters, No. 230-04-31 for Model 230 helicopters, and No. 430-04-31
for Model 430 helicopters, all dated August 27, 2004. The ASBs specify
a repetitive visual inspection every 3 hours time-in-service (TIS) and
a 50-hour inspection of the blade root end around the feathering
bearings for a crack. Transport Canada classified these ASBs as
mandatory and issued AD CF-2004-21, dated October 28, 2004, to ensure
the continued airworthiness of these helicopters in Canada.
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 unsafe condition is likely to exist or develop on other
helicopters of the same type designs. Therefore, this AD is being
issued to prevent loss of a blade and subsequent loss of control of the
helicopter. This AD requires the following:
Within 3 hours time-in-service (TIS), and at specified
intervals, 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 the check for cracked blades. Pilots may
perform these checks 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 at specified intervals, clean and
inspect both sides of each blade for a crack using a 10X or higher
magnifying glass.
If a crack is found even in the paint during a visual
check or during a 50-hour TIS inspection, before further flight, a
further inspection of the blade for a crack is required as follows:
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, before further flight, replace the
blade with an airworthy blade.
If no crack is found in the blade surface, refinish the
blade by applying one coat of MIL-P-23377 or MIL-P-85582 Epoxy
Polyamide Primer so that the primer overlaps the existing coats
[[Page 8]]
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.
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 within 3 hours TIS and 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 require:
\1/4\ hour for a pilot check, assuming 200 a year; and 2
hours for a maintenance inspection, assuming 12 a year at an average
labor rate of $65 per work hour;
Parts cost at about $13,410 per helicopter, assuming one
blade replacement a year. Based on these figures, the estimated total
cost impact of the AD on U.S. operators is $2,842,320 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 your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-19969;
Directorate Identifier 2004-SW-43-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.
Adoption of the Amendment
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 adding a new airworthiness directive to
read as follows:
AD 2004-26-11 Bell Helicopter Textron Canada: Amendment 39-13923.
Docket No. FAA-2004-19969; Directorate Identifier 2004-SW-43-AD.
Applicability: The following helicopter models, identified by
serial number and with the following part number (P/N) tail rotor
blade (blade), installed, certificated in any category.
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Model Serial No. Blade P/N
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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 49105. 222-016-001-123, and -131.
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Compliance: Required as indicated.
To detect a crack in the blade and 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 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 sections 43.11 and 91.417(a)(2)(v).
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Note 1: Bell Helicopter Textron Alert Service Bulletins 222-04-
100, 222U-04-71, 230-04-31, and 430-04-32, all dated August 27,
2004, pertain to the subject of this AD.
(b) If a crack is found in the paint while complying with
paragraph (a) of this AD, before further flight, inspect the blade
by removing the blade and by abrading the area and following the
other requirements in paragraph (c) of this AD.
(c) Within the next 50 hours TIS, unless accomplished
previously, and 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 naptha (C-305)
or detergent (C-318) or equivalents. 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 even a crack is found in the paint, before further
flight, remove the blade.
(2) 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. Abrade the blade surface in a span-wise direction
only.
Note 2: PMB may cause damage to helicopter parts if performed by
untrained personnel. 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.
(i) If a crack is found, before further flight, replace the
blade with an airworthy blade.
(ii) If no crack is found in the blade surface, refinish the
blade by applying one coat of MIL-P-23377 or MIL-P-85582 Epoxy
Polyamide Primer so that the primer overlaps
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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.
(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 paint during a check or inspection.
(f) This amendment becomes effective January 18, 2005.
Note 4: The subject of this AD is addressed in Transport Canada
(Canada) Airworthiness Directive CF-2004-21, dated October 28, 2004.
Issued in Fort Worth, Texas, on December 23, 2004.
Kim Smith,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-28628 Filed 12-30-04; 8:45 am]
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