[Federal Register Volume 85, Number 75 (Friday, April 17, 2020)]
[Rules and Regulations]
[Pages 21318-21320]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-08072]


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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.

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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.

[[Page 21319]]

    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

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):

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 
subsequent 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 information about the subject of this AD. For service 
information identified 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.

[[Page 21320]]

(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.
[FR Doc. 2020-08072 Filed 4-16-20; 8:45 am]
BILLING CODE 4910-13-P


