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2020-08-10 ROBINSON HELICOPTER COMPANY:
Amendment 39-19902; Docket No. FAA-2017-0947; Product Identifier 2017-SW-059-AD. 
(a) APPLICABILITY

    This AD applies  to  Robinson Helicopter Company (Robinson)  Model R44
    and R44  II helicopters,  certificated in  any category,  with a  tail
    rotor blade part number (P/N) C029-1 or P/N C029-2 installed.

(b) UNSAFE CONDITION

    This AD defines the unsafe condition as a crack in a tail rotor blade.
    This condition could result  in the loss  of the tail rotor and subse-
    quent loss of control of the helicopter.

(c) EFFECTIVE DATE

    This AD is effective May 22, 2020.

(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

    Within 50 hours time-in-service after the effective date  of  this  AD
    and thereafter before each flight:

(1) Visually check each tail rotor blade for a crack  in the leading edge,
    paying particular  attention to  the area  in the  most inboard  white
    paint  stripe.  Wipe  the blades  clean, if  necessary, to  ensure any
    potential crack is visible. The actions required by this paragraph may
    be performed by the owner/operator (pilot) holding at least a  private
    pilot  certificate  and  must be  entered  into  the aircraft  records
    showing compliance with this AD  in accordance with 14 CFR  43.9(a)(1)
    through (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.

(2) If there is a crack,  before  further  flight,  replace the tail rotor
    blade.

(f) ALTERNATIVE METHODS OF COMPLIANCE (AMOC)

(1) The Manager,  Los Angeles ACO Branch,  FAA, may approve AMOCs for this
    AD.  Send your proposal to: James Guo, Aerospace Engineer, Los Angeles
    ACO  Branch,  FAA,  3960 Paramount Blvd.,  Lakewood, California 90712;
    telephone 562-627-5357; email james.guo@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate
    or under 14 CFR part 91,  subpart K, the FAA suggests 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) RELATED INFORMATION

    Robinson Helicopter Company R44 Service Bulletin SB-83,  dated May 30,
    2012, which is not incorporated by reference,  contains additional in-
    formation about the subject of this AD. For service information ident-
    ified in this AD,  contact  Robinson Helicopter Company,  2901 Airport
    Drive, Torrance, CA 90505;  telephone 310-539-0508;  fax 310-539-5198;
    or at https://robinsonheli.com/technical-support/. You may view a copy
    of information at the FAA,  Office of the Regional Counsel,  Southwest
    Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.

(h) SUBJECT

    Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor Blades.

Issued  on  April 13, 2020.  Gaetano  A. Sciortino,  Deputy  Director  for
Strategic  Initiatives,  Compliance  &  Airworthiness  Division,  Aircraft
Certification Service.

FOR FURTHER INFORMATION CONTACT:James Guo, Aerospace Engineer, Los Angeles
ACO Branch,  FAA,  3960 Paramount Blvd., Lakewood, California 90712; tele-
phone 562-627-5357; email james.guo@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0947; Product Identifier 2017-SW-059-AD; Amendment
39-19902; AD 2020-08-10]
RIN 2120-AA64

Airworthiness Directives; Robinson Helicopter Company Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Robinson Helicopter Company (Robinson) Model R44 and R44 II
helicopters. This AD was prompted by reports of cracking in certain
tail rotor blades. This AD requires visually checking each tail rotor
blade for a crack. The FAA is issuing this AD to address the unsafe
condition on these products.

DATES: This AD is effective May 22, 2020.

ADDRESSES: For service information identified in this final rule,
contact Robinson Helicopter Company, 2901 Airport Drive, Torrance, CA
90505; telephone 310-539-0508; fax 310-539-5198; or at https://robinsonheli.com/
technical-support/. You may view a copy of the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177.

Examining the AD Docket

You may examine the AD docket on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2017-
0947; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this AD, any comments received, and other information. The address for
Docket Operations is U.S. Department of Transportation, Docket
Operations, M 30, West Building Ground Floor, Room W12 140, 1200 New
Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: James Guo, Aerospace Engineer, Los
Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, California
90712; telephone 562-627-5357; email james.guo@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to Robinson Model R44 and
R44 II helicopters with a tail rotor blade part number (P/N) C029-1 or
P/N C029-2 installed. The NPRM published in the Federal Register on May
23, 2018 (83 FR 23829). The NPRM was prompted by reports of P/N C029-1
and P/N C029-2 tail rotor blades with fatigue cracks at the leading
edge. The cracks were caused by high fatigue stresses due to resonance
when the blades were at high pitch angles from large left pedal inputs.
The NPRM proposed to require visually checking each tail rotor blade
for a crack. The proposed requirements were intended to detect a
cracked tail rotor blade and prevent loss of the blade and subsequent
loss of directional control. The FAA is issuing this AD to address the
unsafe condition on these products.
Since the FAA issued the NPRM, the website address for Robinson
changed. This AD updates that website address.

Comments

The FAA gave the public the opportunity to comment on the NPRM. The
following presents the comments received on the NPRM and the FAA's
response to each comment.
Request: Robinson requested the FAA change the wording in the
Discussion section that states the cracks in tail rotor blades were
caused by ``stresses due to resonance when the blades were at high
pitch angles from large left pedal inputs'' to ``stresses during
maneuvers with large left pedal inputs.''
FAA Response: The FAA disagrees. The wording in the NPRM provides
greater detail with regard to the mechanics of the cause of the
cracking.
Request: Robinson requested the FAA change the wording in the
Discussion section that describes the proposed actions' intentions by
adding the word ``possible'', which would read as follows: ``prevent
possible loss of the blade.'' Robinson states that even with a crack,
loss of the blade is possible, but not certain.
FAA Response: The FAA disagrees. The unsafe condition described in
this AD is a crack in the tail rotor blade. The current wording does
not state the helicopter will lose a tail rotor blade but rather loss
of a blade could occur. The description of the unsafe condition states
that the condition ``could result in the loss of the tail rotor.''
Request: Robinson requested the FAA correct the two instances of
the wording ``tail leading edge'' by deleting the word ``tail.'' The
first instance is in the Proposed AD Requirements section and the
second instance is in the Required Actions paragraph.
FAA Response: The FAA agrees and has made these corrections.
Request: Robinson requested that the FAA change the Applicability
paragraph by adding the following: ``Tail rotor blade part number is
visible on data plate located between bearings in blade root.''
FAA Response: The FAA disagrees because the addition is
unnecessary. Parties may refer to the data plate or the aircraft's
records to determine which part-numbered tail rotor blades are
installed. If they are uncertain about the location of the data plate,
they can refer to service information documents that interested parties
have access to through their normal course of business.
Request: Robinson requested that the FAA change the wording in the
Unsafe Condition paragraph to state, ``This AD defines the unsafe
condition as a possible crack in the tail rotor blade'' because not all
blades have a crack.
FAA Response: The FAA disagrees. The unsafe condition that is being
addressed is a crack in a blade.
Request: Robinson requested that the FAA change the wording in the
Required Actions section from the checks of the tail rotor blades may
be conducted ``by the owner/operator'' to ``by an owner/operator.''
FAA Response: The FAA disagrees. The language requested by the
commenter would unacceptably broaden the AD requirement. The FAA
intended to allow the owner or operator of the aircraft, who holds at
least a private pilot certificate, to perform the check when
maintenance personnel are not present. The requested change in language
may be interpreted to allow a pilot to perform the check on any
aircraft, including aircraft that the pilot does not own or operate.

Request: Robinson requested the FAA change the wording in the
Required Actions paragraph from: ``If there is a crack, before further
flight, replace the tail rotor blade'' to ``If a crack is detected,
replace tail rotor blade before further flight.''
FAA Response: The FAA disagrees. The wording in the NPRM
sufficiently explains that if there is a crack, the tail rotor blade
must be replaced.

FAA's Determination

The FAA has reviewed the relevant information, considered the
comments received, and determined that an unsafe condition exists and
is likely to exist or develop on other products of the same type design
and that air safety and the public interest require adopting the AD
requirements as proposed with the changes described previously. These
changes are consistent with the intent proposed in the NPRM for
correcting the unsafe condition and will not increase the economic
burden on any operator nor increase the scope of the AD.

Related Service Information

The FAA has reviewed Robinson SB-83, dated May 30, 2012 (SB-83),
which specifies, within 10 flight hours or by June 30, 2012, whichever
occurs first, inserting a caution page into the Pilot's Operating
Handbook. The caution page specifies inspecting the leading edges of
each tail rotor blade for a crack before each flight. The caution page
also advises that to reduce fatigue stress damage to the tail rotor
blades, pilots should avoid maneuvers that require large left pedal
inputs. SB-83 specifies that the caution page may be removed when the
tail rotor blades are replaced with tail rotor blade P/N C029-3.

Costs of Compliance

The FAA estimates that this AD affects 1,631 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
Visually checking the tail rotor blades for a crack takes about 0.2
work-hour for an estimated cost of $17 per helicopter and $27,727 for
the U.S. fleet per check cycle.
Replacing a tail rotor blade takes about 2 work-hours and parts
cost about $3,080 for an estimated replacement cost of $3,250 per
blade.

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.
The FAA is 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

The FAA 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) Will not affect intrastate aviation in Alaska, 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.

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

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]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):