[Federal Register Volume 78, Number 211 (Thursday, October 31, 2013)]
[Rules and Regulations]
[Pages 65195-65198]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-25702]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0486; Directorate Identifier 2010-SW-031-AD;
Amendment 39-17622; AD 2013-20-16]
RIN 2120-AA64
Airworthiness Directives; MD Helicopters, Inc. (MDHI) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for MDHI
Model MD900 helicopters with certain main rotor blade (MRB) retention
bolts (bolts) installed. This AD requires a daily check of the position
of each bolt, a daily check and a repetitive inspection for a gap in
each bolt, and, if necessary, removing and inspecting the bolt for a
crack and replacing any cracked bolt with an airworthy bolt. This AD
was prompted by multiple reports of in-service bolt failures. The
actions are intended to prevent failure of a bolt, which could lead to
loss of MRB structural integrity and subsequent loss of control of the
helicopter.
DATES: This AD is effective December 5, 2013.
ADDRESSES: For service information identified in this AD, contact MDHI,
Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615,
Mesa, AZ 85215-9734, telephone (800) 388-3378, fax (480) 346-6813, or
at http://www.mdhelicopters.com. 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.
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
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 (phone: 800-647-5527) is U.S. Department of
Transportation, Docket Operations Office, M-30, West Building Ground
Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aerospace Engineer, FAA,
Los Angeles Aircraft Certification Office, Airframe Branch, ANM-120L,
3960 Paramount Blvd., Lakewood, CA 90712, telephone (562) 627-5233, fax
(562) 627-5210, email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On June 14, 2013, at 78 FR 35773, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to add an AD that would apply to MDHI Model MD900
helicopters with certain bolts installed. The NPRM proposed to require
a daily check of the position of each bolt, a daily check and a
repetitive inspection for a gap in each bolt, and, if necessary,
removing and inspecting the bolt for a crack and replacing any cracked
bolt with an airworthy bolt. The NPRM was prompted by multiple reports
of in-service bolt failures. The proposed requirements were intended to
prevent failure of a bolt, which could lead to loss of MRB structural
integrity and subsequent loss of control of the helicopter.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 35773,
June 14, 2013).
FAA's Determination
We have reviewed the relevant information and determined that an
unsafe condition exists and is likely to exist or develop on other
helicopters of the same type designs and that air safety and the public
interest require adopting the AD requirements as proposed.
Related Service Information
MDHI issued Alert Service Bulletin SB900-116R1, dated April 9, 2010
(ASB SB900-116R1), which supersedes ASB SB900-116, dated February 24,
2010 (ASB SB900-116).
ASB SB900-116 specifies a repetitive check of the blade retention
bolts, part number (P/N) 900R3100001-103 and 900R3100001-105, for a gap
and, depending on the outcome of the inspection, removing and
inspecting the bolt for damage. The ASB also specifies a repetitive
force check of each bolt, P/N 900R3100001-103, and a torque check of
each bolt, P/N 900R3100001-105. Lastly, the ASB specifies a daily
preflight check of each bolt to examine the position of the bolt and
for a gap, and, if any bolt has moved up or down or if there was no
gap, removing and inspecting the bolt.
Superseding ASB SB900-116R1 retains the same specifications as ASB
SB90016, except that it revises the
[[Page 65196]]
interval for the bolt force and torque checks from 4-6 flight-hours to
8-10 flight-hours. ASB SB90016R1 also revises the change of force or
torque from not more than 10 percent to not more than 10
percent.
Differences Between This AD and the Service Information
This AD uses the term ``inspect'' when describing the action of
inspecting a bolt for a crack and inspecting for a gap between the
thrust washer and the retainer. The ASB uses the term ``check.''
Costs of Compliance
We estimate that this AD will affect 29 helicopters in the U.S.
registry. We estimate that operators may incur the following costs to
comply with this AD: The average labor rate is $85 per work hour. It
will take about .5 work hour to do a gap inspection of each bolt. It
will take about 1 work hour to replace a cracked bolt and the required
parts will cost $800 at a total cost per helicopter of $928.
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 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):
2013-20-16 MD Helicopters, Inc. (MDHI): Amendment 39-17622; Docket
No. FAA-2013-0486; Directorate Identifier 2010-SW-031-AD.
(a) Applicability
This AD applies to Model MD 900 helicopters with a main rotor
blade retention bolt (bolt), part number (P/N) 900R3100001-103 or
900R3100001-105, installed; certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as bolt failure. This
condition could result in loss of main rotor blade structural
integrity and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective December 5, 2013.
(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) Before the first flight of each day:
(i) Visually check each bolt for failure. Failure of a bolt may
be indicated by movement of the bolt out of the bolt hole or by
inconsistent extension of the bolt above or below the other bolts
being inspected (a failed bolt migrates out of the bolt hole).
(ii) Visually check for a gap between the thrust washer and the
retainer, P/N 900R2100009-101 or -103. The thrust washer is depicted
as item 2 and the retainer is depicted as item 8 in Figure 1 to
paragraph (e) of this AD.
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(iii) The actions required by paragraphs (e)(1)(i) and
(e)(1)(ii) may be performed by the owner/operator (pilot) holding at
least a private pilot certificate and must be entered into the
aircraft maintenance records showing compliance with this AD in
accordance with 14 CFR 43.9(a)(1)-(4) and 14 CFR 91.417(a)(2)(v).
The record must be maintained as required by 14 CFR 91.417, 121.380,
or 135.439.
(iv) If there is any indication of bolt failure or if there is
no gap between the thrust washer and retainer, before further
flight, remove and inspect the bolt for a crack. Replace any cracked
bolt with an airworthy bolt.
(2) Within 300 hours time-in-service (TIS), and thereafter at
intervals not to exceed 300 hours TIS, inspect each bolt for a gap
between the thrust washer and the retainer.
(i) Determine whether an O-ring is installed. Install any
missing O-ring.
(ii) If there is no gap between the thrust washer and retainer,
before further flight, remove and inspect the bolt for a crack.
Replace any cracked bolt with an airworthy bolt.
(iii) If there is a gap between the thrust washer and retainer,
measure the gap in two locations, 180 degrees apart, with a feeler
gage. If the gap is more than 0.100 inch (2.54 mm) at either
location, before further flight, remove and inspect the bolt for a
crack. Replace any cracked bolt with an airworthy bolt.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office,
Airframe Branch (ANM-120L), FAA, may approve AMOCs for this AD. Send
your request to Roger Durbin, Aerospace Engineer, FAA, Los Angeles
Aircraft Certification Office, Airframe Branch, ANM-120L, 3960
Paramount Blvd., Lakewood, CA 90712, telephone (562) 627-5233, fax
(562) 627-5210, email [email protected].
[[Page 65198]]
(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.
(g) Additional Information
MDHI Alert Service Bulletin SB900-116R1, dated April 9, 2010,
which supersedes MDHI Alert Service Bulletin SB SB900-116, dated
February 24, 1010, neither of which is incorporated by reference,
contains additional information about the subject of this AD. For
service information identified in this AD, contact MDHI, Attn:
Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615,
Mesa, AZ 85215-9734, telephone (800) 388-3378, fax (480) 346-6813,
or at http://www.mdhelicopters.com. You may review copies of the
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas.
(h) Subject
Joint Aircraft System Component: 6210: Main rotor blade
retention bolts.
Issued in Fort Worth, Texas, on September 27, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-25702 Filed 10-30-13; 8:45 am]
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