[Federal Register Volume 77, Number 178 (Thursday, September 13, 2012)]
[Rules and Regulations]
[Pages 56528-56533]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-22564]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0896; Directorate Identifier 2010-SW-070-AD;
Amendment 39-17173; AD 2012-17-10]
RIN 2120-AA64
Airworthiness Directives; Various Restricted Category Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for various
restricted category Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-
1F, UH-1H, UH-1L, and UH-1P helicopters with certain main rotor (M/R)
blade assemblies installed, to require inspecting the grip plates,
doublers, and upper and lower surfaces of the M/R blades in the area
between blade stations 24.5 and 40 for an edge void, corrosion, or a
crack. This AD is prompted by several reports of fatigue cracks on M/R
blades installed on Bell Helicopter Textron, Inc. (Bell) Model 212
helicopters. These same part-numbered M/R blades may also be installed
on certain FAA-approved modified restricted category helicopters. These
actions are intended to detect an edge void, corrosion, or a crack on
an M/R blade, which could lead to loss of the M/R blade and subsequent
loss of control of the helicopter.
DATES: This AD becomes effective September 28, 2012.
We must receive comments on this AD by November 13, 2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket: You may examine the AD docket on the
Internet at http://www.regulations.gov or in person at the Docket
Operations Office
[[Page 56529]]
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the economic evaluation, any
comments received, and other information. The street address for the
Docket Operations Office (telephone 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
For service information identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone
(817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may review a copy of the referenced service information at
the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT: Michael Kohner, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222-5170;
email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, explain the reason for any recommended change, and
include supporting data. To ensure the docket does not contain
duplicate comments, commenters should send only one copy of written
comments, or if comments are filed electronically, commenters should
submit them only one time. We will file in the docket all comments that
we receive, as well as a report summarizing each substantive public
contact with FAA personnel concerning this rulemaking during the
comment period. We will consider all the comments we receive and may
conduct additional rulemaking based on those comments.
Discussion
This AD is prompted by several reports of fatigue cracks on M/R
blades installed on Bell Model 212 helicopters. The cracks were found
in the lower skin, doublers, and box beam at the M/R blade attachment
bolt hole, and through the lower grip plate at blade station (BS) 36.
Because the fatigue cracks were discovered on M/R blades installed on
the Bell Model 212 helicopters, we issued AD No. 2010-03-03, Amendment
39-16186 (75 FR 5681, February 4, 2010) (AD 2010-03-03) for certain
Bell Model 205B and 212 helicopters. That AD required visually
inspecting the M/R blades for an edge void, corrosion, or a crack.
After issuing that AD, we received another report of a fatigue crack on
a M/R blade installed on a Model 212 helicopter. Further analysis by
the manufacturer revealed that the inspections required by AD 2010-03-
03 needed to be expanded and performed at an increased frequency, and
on additional part-numbered M/R blades which can also be installed on
other Bell model helicopters. We then issued AD No. 2011-23-02 (76 FR
68301, November 4, 2011) (AD 2011-23-02), which superseded AD 2010-03-
03. AD 2011-23-02 retained the requirements of the superseded AD,
increased the frequency and scope of the inspections required by that
AD, and expanded the applicability to include the Model 205A-1 and 210
helicopters, additional M/R blade part numbers, and all helicopter
serial numbers for the affected models.
Since the issuance of AD 2011-23-02, we have determined that the
same part-numbered M/R blades can also be installed on certain FAA-
approved modified restricted category helicopters. Therefore, we are
mandating the inspection requirements for the applicable restricted
category helicopters. The actions specified in this AD are intended to
detect an edge void, corrosion, or a crack on an M/R blade, which could
lead to loss of the M/R blade and subsequent loss of control of the
helicopter.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other helicopters of these same type
designs.
Related Service Information
Bell has issued Alert Service Bulletin (ASB) No. 205B-08-51 dated
January 11, 2011 (ASB 205B-08-51) for Model 205B helicopters, ASB No.
210-08-03 dated January 10, 2011 (ASB 210-08-03) for the Model 210
helicopters, and ASB No. 212-08-130 dated January 11, 2011 (ASB 212-08-
130) for Model 212 helicopters, all revision B. The ASBs describe
procedures to detect an edge void, corrosion, or a crack in the upper
and lower grip plates, doublers, and blade skins of the M/R blade
between blade stations 24.5 and 85.
AD Requirements
This AD requires, within 25 hours time-in-service (TIS), and
thereafter at intervals not to exceed 25 hours TIS, the following
actions:
Washing the upper and lower M/R blade surfaces using a
solution of cleaning compound and water;
Visually inspecting the upper and lower grip plates,
doublers, and remaining surfaces of the M/R blade in an area from blade
stations 24.5 to 40, including the entire width of the M/R blade chord
width for an edge void, any corrosion, or a crack;
Wiping each of the bond lines at the edges of both grip
plates and each of the layered doublers with an alcohol-soaked cloth
for their entire length and chord width and, using a 3x power or higher
magnifying glass and a bright light, visually inspecting each of the
bond lines on the upper and lower surfaces of the M/R blade for an edge
void, any corrosion, or any edge delamination, as indicated by a crack
in the paint finish.
If there is an edge delamination or a crack in the paint
finish, removing paint from areas in which an edge delamination along
any bond line of a grip plate or doubler or a crack in the M/R blade
paint finish is discovered to determine if an edge void or a crack
exists in the M/R blade and, if there is not an edge void or a crack,
refinishing the sanded area;
Applying a light coat of preservative oil to all surfaces
of the M/R blade;
Replacing any M/R blade that has an edge void or any
corrosion with an airworthy M/R blade or repairing the M/R blade if the
damage is within the maximum repair damage limits;
Replacing any M/R blade that has a crack in any grip plate
or doubler with an airworthy M/R blade; and
Replacing any M/R blade that has a crack in the M/R blade
skin with an airworthy M/R blade, or repairing the M/R blade if the
damage is within the maximum repair damage limits.
Differences Between This AD and the Service Information
This AD applies to various restricted category Model HH-1K, TH-1F,
TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters;
ASB 205B-08-51, ASB 210-08-03, and ASB 212-08-130 apply to Model 205B,
210, and 212 helicopters, respectively.
This AD also differs from the ASBs as follows:
We do not include the requirement to inspect for a dark
line along any of
[[Page 56530]]
the bond lines after wiping with an alcohol-soaked cloth to detect an
edge void or edge delamination as stated in the ASBs. The alcohol is
only being used as a cleaning agent for the purposes of this AD.
This AD requires inspecting for an edge void, a crack, or
any corrosion in an area from blade stations 24.5 to 40, including the
entire width of the M/R blade chord, while the ASBs require inspecting
from blade stations 24.5 to 85. This AD includes the inspections of the
bondlines for their entire length and chord width for an edge
delamination or for a crack in the paint finish, while the ASB
inspections do not.
The ASBs use the phrase ``bond lines between doublers,
grip plates, and skin'' to describe the bond lines, and we use ``bond
lines at the edges of both grip plates and each of the layer
doublers.''
The ASBs use the phrase ``cracks in the bond lines between
doublers or grip plates'' to describe a separation of the doubler or
grip plate along an edge, and we use the term ``edge delamination.''
Costs of Compliance
We estimate that this AD will affect 25 helicopters of U.S.
Registry.
We estimate that operators may incur the following costs in order
to comply with this AD. Washing and visually inspecting each M/R blade
requires one work hour at an average labor rate of $85 per hour, for a
cost per helicopter of $85 and a total cost to the U.S. operator fleet
of $2,125 per inspection cycle. If an edge void, corrosion, or a crack
is found, replacing an M/R blade with an airworthy M/R blade requires
approximately 24 work hours at an average labor rate of $85 per hour,
and required parts cost $121,875, for a total cost for each M/R blade
replacement of $123,915.
FAA's Justification and Determination of the Effective Date
The short compliance time is required because the previously
described critical unsafe condition can adversely affect the structural
integrity and controllability of the helicopter. In addition, the
various restricted category helicopters are high usage aircraft, and
they could reach 100 hours TIS within 60 days. Therefore, the actions
described previously are required within 25 hours TIS, a short
compliance time, and are to be repeated thereafter at intervals not to
exceed 25 hours TIS, and this AD must be issued immediately.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
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.
Regulatory Findings
We 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, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
4. 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 and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
Reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2012-17-10 Various Restricted Category Helicopters: Amendment 39-
17173; Docket No. FAA-2012-0896; Directorate Identifier 2010-SW-070-
AD.
(a) Applicability
This AD applies to restricted category Model HH-1K, TH-1F, TH-
1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters
with a main rotor (M/R) blade, part number (P/N) 204-012-001-023 or
-033; 210-015-001-101; 212-015-501-005, -111, -113, -115, -117, -
119, or -121, installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as an edge void, corrosion,
or a crack on an M/R blade. This condition could lead to loss of the
M/R blade and subsequent loss of control of the helicopter.
(c) Effective Date
This airworthiness directive (AD) becomes effective September
28, 2012.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) Within 25 hours time-in-service (TIS), and thereafter at
intervals not to exceed 25 hours TIS:
(i) Wash the upper and lower surfaces of each affected M/R blade
with a solution of cleaning compound (C-318) and water. Rinse
thoroughly and wipe dry.
(ii) Using a 3x power or higher magnifying glass and a bright
light, on each affected M/R blade, in an area from blade stations
24.5 to 40, including the entire width of the M/R blade chord, as
depicted in Figure 1 to Paragraph (e) of this AD:
[[Page 56531]]
[GRAPHIC] [TIFF OMITTED] TR13SE12.001
(A) Visually inspect the upper and lower grip plates and
doublers of the M/R blade for an edge void, any corrosion, or a
crack.
(B) Visually inspect the remaining upper and lower surfaces of
the M/R blade for an edge void, any corrosion, or a crack.
Note 1 to paragraphs (e)(1)(ii) and (e)(1)(iv): The inspections
required by paragraphs (e)(1)(ii) and (e)(1)(iv) of this AD do not
require removal of the M/R blades from the M/R hub and can be
accomplished while the M/R blades are installed on the helicopter.
Note 2 to paragraph (e)(1)(ii): Crack indications on an actual
M/R blade are shown in Figure 2 to Paragraph (e) of this AD.
[[Page 56532]]
[GRAPHIC] [TIFF OMITTED] TR13SE12.002
(iii) Wipe each of the bond lines at the edges of both grip
plates and each of the layered doublers (bond lines) on the upper
and lower surfaces of each affected M/R blade with an alcohol-soaked
cloth (C-385) for their entire length and chord width. Wipe dry with
a clean cloth.
(iv) Using a 3x power or higher magnifying glass and a bright
light, visually inspect each of the bond lines on the upper and
lower surfaces of the M/R blade for their entire length and chord
width for an edge void, any corrosion, or any edge delamination, as
indicated by a crack in the paint finish. An edge delamination is
defined as a separation of the detail parts along an edge.
Note 3 to paragraph (e)(1)(iv): A crack in the paint finish
which follows the outline of a grip plate or doubler may indicate a
possible edge void.
(v) If there is any edge delamination along any bond line of a
grip plate or doubler, or a crack in the paint finish, before
further flight, remove the paint in the affected area by lightly
sanding with 180-220 grit paper in a span-wise direction to
determine if there is an edge void, or if the grip plate, doubler,
or skin is cracked. If any parent material is removed during the
sanding operation, replace the M/R blade with an airworthy M/R blade
or repair the M/R blade if the amount of parent material removed is
within the maximum repair damage limits. If there is no edge void or
crack, refinish the sanded area.
Note 4 to paragraphs (e)(1)(v) and (e)(2): The maximum repair
damage limits are contained in the applicable Component and Repair
Overhaul Manual.
(vi) If there is no edge void, corrosion, or crack, apply a
light coat of preservative oil (C-125) to all surfaces of each
affected M/R blade.
(2) If an edge void, any corrosion, or a crack is discovered
during any inspections in paragraph (e)(1) of this AD, before
further flight, accomplish the following:
(i) If there is an edge void, determine the depth and length
using a .0015 inch feeler gauge.
(ii) If there is an edge void in a grip plate or doubler near
the outboard tip, tap inspect the affected area to determine the
size and shape of the void.
(iii) Repair the M/R blade if the edge void is within the
maximum repair damage limits or replace the M/R blade with an
airworthy M/R blade.
[[Page 56533]]
(iv) If there is any corrosion, replace the M/R blade with an
airworthy M/R blade or repair the M/R blade if the damage is within
the maximum repair damage limits.
(v) If there is a crack in any grip plate or doubler, replace
the M/R blade with an airworthy M/R blade.
(vi) If there is a crack in the M/R blade skin, replace the M/R
blade with an airworthy M/R blade, or repair the M/R blade if the
damage is within the maximum repair damage limits.
(f) Special Flight Permits
Special flight permits will be permitted for flights to an
authorized inspection and repair facility provided the one-time
ferry flight does not exceed 5 hours TIS and is for the
accomplishment of an inspection only.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Kohner,
Aviation Safety Engineer, Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX
76137; telephone (817) 222-5170; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(h) Additional Information
Bell Helicopter Alert Service Bulletin (ASB) No. 205B-08-51
Revision B, dated January 11, 2011, for Model 205B helicopters, ASB
No. 210-08-03 Revision B, dated January 10, 2011 for the Model 210
helicopters, and ASB No. 212-08-130 Revision B, dated January 11,
2011, for Model 212 helicopters, which are not incorporated by
reference, contain additional information about the subject of this
AD. For service information identified in this AD, contact Bell
Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101;
telephone (817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may review a copy of this service
information at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 6210: Main Rotor
Blades.
Issued in Fort Worth, Texas, on August 21, 2012.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-22564 Filed 9-12-12; 8:45 am]
BILLING CODE 4910-13-P