[Federal Register Volume 76, Number 136 (Friday, July 15, 2011)]
[Rules and Regulations]
[Pages 41662-41665]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-17421]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0695; Directorate Identifier 2011-SW-001-AD;
Amendment 39-16740; AD 2011-14-05]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc. Model MD900
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes an existing airworthiness directive
(AD) for MD Helicopters, Inc. (MDHI) Model MD900 helicopters. That AD
currently requires visually inspecting the main rotor lower hub
assembly (lower hub) for a crack, and if you find a crack, before
further flight, replacing the unairworthy lower hub with an airworthy
lower hub. Additionally, within 10 days of finding a cracked lower hub,
the existing AD requires reporting the finding to the Los Angeles
Aircraft Certification Office (LAACO). That AD was prompted by two
reports of cracks detected in the hub in the area near the flex beam
bolt hole locations during maintenance on two MDHI Model MD900
helicopters. Since we issued that AD, we determined that one
manufacturer had incorrectly inserted flanged bushings into the lower
hub bore that resulted in local corrosion, leading to fatigue cracking.
Examination of lower hubs from the other manufacturer shows correct
bushing installation. Therefore, this amendment limits the
applicability to the affected lower hubs; retains the visual inspection
but at a different compliance time; adds an eddy current inspection;
retains the requirement to replace a cracked lower hub with an
airworthy lower hub before further flight; and removes the requirement
to report to the LAACO. The actions specified by this AD are intended
to detect a crack in the lower hub and prevent failure of the lower hub
and subsequent loss of control of the helicopter.
DATES: This AD is effective August 1, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of August 1,
2011.
We must receive any comments on this AD by September 13, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact MD
Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell
Rd., Mail Stop M615, Mesa, AZ 85215-9734, telephone 1-800-388-3378, fax
480-346-6813, or at http://www.mdhelicopters.com.
[[Page 41663]]
Examining the AD 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 street address for
the Docket Office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Eric Schrieber, Aviation Safety
Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe
Branch, 3960 Paramount Blvd., Lakewood, California 90712-4137,
telephone (562) 627-5348, fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Discussion
On August 19, 2010, we issued Emergency AD (EAD) 2010-18-51. That
EAD was prompted by two reports of cracks detected in the lower hub
near the flex beam bolt hole location during maintenance. That EAD
required, within 4 hours time-in-service (TIS), visually inspecting the
lower hub for a crack and, if you find a crack, before further flight,
replacing the lower hub with an airworthy lower hub and, within 10
days, reporting a cracked lower hub to the LAACO. We superseded EAD
2010-18-51 with EAD 2010-18-52, issued August 23, 2010, upon
discovering a typographical error in the ``Applicability'' section of
the EAD in the lower hub part number (P/N). EAD 2010-18-52 contained
the same requirements as EAD 2010-18-51 but corrected the P/N for the
lower hub.
Actions Since That AD Was Issued
Since we issued the AD, 5 additional lower hubs were found cracked.
We determined that one manufacturer of lower hubs with serial numbers
(S/Ns) beginning with 5009 (e.g., 5009-XXXX) had incorrectly inserted
flanged bushings into the lower hub bore. This condition resulted in
local corrosion leading to fatigue cracking. Examination of lower hubs
from the other manufacturer shows correct bushing installation.
Relevant Service Information
We reviewed MDHI Service Bulletin SB900-117, dated January 14, 2011
(SB). The SB specifies an initial 100-hour and recurring 300-hour
visual and eddy current inspections of the lower hub for a crack and,
if there is a crack, replacing the lower hub with an airworthy lower
hub. The inspections would be done at the stated intervals or at the
next annual inspection, whichever occurs first. The SB also specifies
replacing an affected lower hub within 3 years after the date of the
SB.
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 this same type
design.
AD Requirements
This AD requires a visual inspection, and if necessary, an eddy
current inspection of the lower hub for a crack. If there is a crack,
the AD requires replacing the lower hub with an airworthy lower hub.
This AD requires accomplishing these actions by following specified
portions of the service information described previously, except as
discussed under ``Differences Between the AD and the Service
Information.''
Change to Existing AD
This superseding AD changes the compliance time for the visual
inspection and adds an eddy current inspection of the lower hub for a
crack. This AD also removes the reporting requirement to the LAACO and
the requirement for an OMB control number. This AD also reduces the
applicability to only those helicopters with certain serial-numbered
lower hubs installed.
Differences Between the AD and the Service Information
This AD does not require contacting the manufacturer or returning
the lower hub assembly with a certain report. This AD also does not
require the 300-hour inspection or replacing the lower hub within 3
years from the date of the SB because these actions do not fit our
criteria for a Final rule, request for comments.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because the
previously described unsafe condition can adversely affect the
structural integrity and controllability of the helicopter. The
inspection is required within 100 hours TIS or during the annual
inspection, whichever occurs first, unless done within the last 200
hours TIS. Since the affected helicopters could reach 100 hours TIS
within 1 month, we find that notice and opportunity for prior public
comment are impracticable and that good cause exists for making this
amendment effective in less than 30 days.
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 before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2011-0695 and directorate identifier 2011-SW-001-
AD at the beginning of your comments. We specifically invite comments
on the overall regulatory, economic, environmental, and energy aspects
of this AD. We will consider all comments received by the closing date
and may amend this AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 12 helicopters of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
1 work hour to visually inspect the 1 work-hour x $85 per N/A........................................ $85 $1,020.
hub. hour = $85.
[[Page 41664]]
1 work hour to eddy current inspect 1 work-hour x $85 per N/A........................................ $85 $1,020.
the lower hub [new action]. hour = $85.
Required parts and labor to replace a 11 work hours x 85 per $12,480 per hub............................ $13,415 $160,980.
lower hub. hour = $935.
-----------------------------------------------------------------------------------------------------------------
Total............................. $1,105................... $12,480.................................... $13,585 $163,020 assuming the
lower hubs are replaced
for the entire fleet.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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
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 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, 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.
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 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. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2010-18-52, Amendment 39-16515 (75 FR 69862, November 16, 2010) and
adding the following new AD:
2011-14-05 MD HELICOPTERS, INC.: Amendment 39-16740; Docket No. FAA-
2011-0695; Directorate Identifier 2011-SW-001-AD.
Effective Date
(a) This AD is effective August 1, 2011.
Affected ADs
(b) This AD supersedes AD 2010-18-52, Amendment 39-16515, Docket
No. FAA-2010-1126; Directorate Identifier 2010-SW-078-AD.
Applicability
(c) Model MD900 helicopters with main rotor lower hub assembly
(lower hub), part number (P/N) 900R2101008-107, serial numbers (S/
Ns) that begin with 5009, certificated in any category.
Unsafe Condition
(d) This amendment is prompted by the determination that a
certain manufacturer had incorrectly inserted the flanged bushings
into the lower hub bore. The actions specified by this AD are
intended to detect a crack in the lower hub and prevent failure of
the hub and subsequent loss of control of the helicopter.
Compliance
(e) Within 100 hours time-in-service (TIS) or during the next
annual inspection, whichever occurs first, unless done within the
last 200 hours TIS:
(1) Visually inspect the sides and bottom of the area between
the arms for the centering bearing and the areas adjacent to the
bushings of the lower hub assembly for a crack. If there is a crack,
before further flight, replace the lower hub with an airworthy lower
hub.
(2) If the lower hub is not replaced as a result of the visual
inspection required by paragraph (e)(1) of this AD, eddy current
inspect the lower hub for a crack by following the Accomplishment
Instructions, paragraphs 2.A(2) through 2.A.(10)., of MD Helicopters
Inc. Service Bulletin SB900-117, dated January 14, 2011 (SB). If
there is a crack, before further flight, replace the lower hub with
an airworthy hub.
(f) The eddy current inspection required by paragraph (e)(2) of
this AD must be done by a Level II technician with ASNT-TC-1A, CEN
EN 4179, MIL-STD-410, NAS410, or equivalent certification in eddy
current inspections. The technician must have done an eddy current
inspection in the last 12 months.
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, Los Angeles Aircraft Certification Office
(LAACO), FAA, has the authority to approve AMOCs for this AD, if
requested, using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the LAACO, send it to the
attention of the person identified in the Additional Information
section of this AD.
(2) Before using any approved AMOC, we request that you notify
your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding district office.
Additional Information
(h) For more information about this AD, contact Eric Schrieber,
Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification
Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California
90712-4137, telephone (562) 627-5348, fax (562) 627-5210.
Material Incorporated by Reference
(i)(1) Inspect the main rotor lower hub assembly for a crack by
following the specified portions of MD Helicopter, Inc. Service
Bulletin SB 900-117, dated January
[[Page 41665]]
14, 2011. The Director of the Federal Register approved the
incorporation by reference of the service information, under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact MD
Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell
Rd., Mail Stop M615, Mesa, AZ 85215-9734, telephone 1-800-388-3378,
fax 480-346-6813, or at http://www.mdhelicopters.com.
(3) 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 an
NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Subject
(j) The Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code is 6220: Main Rotor Head.
Issued in Fort Worth, Texas, on June 21, 2011.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-17421 Filed 7-14-11; 8:45 am]
BILLING CODE 4910-13-P