[Federal Register Volume 87, Number 222 (Friday, November 18, 2022)]
[Rules and Regulations]
[Pages 69161-69164]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-25030]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0286; Project Identifier AD-2021-01081-R; 
Amendment 39-22223; AD 2022-22-08]
RIN 2120-AA64


Airworthiness Directives; Bell Textron Canada Limited (Type 
Certificate Previously Held by Bell Helicopter Textron Canada Limited) 
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 
Bell Textron Canada Limited (type certificate previously held by Bell 
Helicopter Textron Canada Limited) Model 206L, 206L-1, 206L-3, and 
206L-4 helicopters with a certain part-numbered main rotor (M/R) blade 
installed under Supplemental Type Certificate (STC) SR02684LA. This AD 
was prompted by delamination of M/R blades. This AD requires a 
repetitive inspection for delamination, and depending on the results, 
removing the M/R blade from service and reporting certain information. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective December 23, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 23, 
2022.

ADDRESSES: For service information identified in this final rule, 
contact Dean Rosenlof, Van Horn Aviation, LLC, 1510 West Drake Drive, 
Tempe, AZ, 85283, United States; phone: (480) 483-4202; email: 
[email protected]. You may view this service information at the 
FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood 
Pkwy., Room 6N-321, Fort Worth, TX 76177. For information on the 
availability of this material at the FAA, call (817) 222-5110. It is 
also available at regulations.gov by searching for and locating Docket 
No. FAA-2022-0286.

Examining the AD Docket

    You may examine the AD docket at regulations.gov by searching for 
and locating Docket No. FAA-2022-0286; 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 final rule, 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: Payman Soltani, Aerospace Engineer, 
Airframe Section, Los Angeles ACO Branch, Compliance & Airworthiness 
Division, FAA, 3960 Paramount Blvd., Lakewood, CA 90712; telephone 
(562) 627-5313; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to Bell Textron Canada 
Limited Model 206L, 206L-1, 206L-3, and 206L-4 helicopters with a 
certain part-numbered M/R blade installed under STC SR02684LA. The NPRM 
published in the Federal Register on March 24, 2022 (87 FR 16652). The 
NPRM was prompted by testing by Van Horn Aviation, LLC (Van Horn), 
which revealed the potential for delamination in M/R blade part number 
(P/N) 20633000-101. Delaminations were then confirmed by inspection of 
in-service M/R blades. Testing by Van Horn confirmed that the 90[deg] 
plies fail in spanwise tension (normal to the fiber

[[Page 69162]]

direction) at the inboard end of the weight receptacle near M/R blade 
station 186.0. Delamination then propagates outboard from M/R blade 
station 186.0 at the interface between the 0[deg] and 90[deg] plies. 
According to Van Horn, fatigue testing has shown that the delamination 
initiates almost immediately and progresses slowly in a stable, 
predictable manner. The delamination has been found to develop first on 
the lower surface and grow outboard from the inboard end of the weight 
receptacle and forward of the balance weight pocket. After 
approximately 4 to 6 inches growth of the delamination on the lower 
surface, a similar delamination becomes detectable on the M/R blade 
upper surface. Should the delaminations continue to grow to the point 
of static overload, the receptacle could depart the M/R blade. In the 
NPRM, the FAA proposed to require, at specified intervals, removing the 
affected M/R blade, drawing rectangular inspection areas ``Zone 1'' and 
``Zone 2'' with a permanent marker, tap inspecting the inspection areas 
for delamination, marking and measuring the length of any delamination, 
and depending on the results, removing the M/R blade from service. The 
NPRM also proposed to require reporting certain information to Van 
Horn. The FAA is issuing this AD to address the unsafe condition on 
these products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from one commenter, Van Horn. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment.

Request for Changes to the Measurements of Inspection Areas

    Van Horn stated that the M/R blade stations indicated for 
inspections are incorrect in the proposed AD and requested the FAA 
revise the required actions to change the M/R blade stations for ``Zone 
1'' and ``Zone 2.'' However, the measurements Van Horn included in the 
comment in the AD docket to correct the M/R blade stations for ``Zone 
1'' and ``Zone 2'' were also incorrect. Van Horn then contacted the FAA 
to correct these measurements; a record of this ex parte contact is 
included in the AD docket. For information on locating the docket, see 
``Examining the AD Docket.'' According to Van Horn's revised comments, 
``Zone 1'' described in the NPRM as M/R blade stations 186.0 and 191.0, 
beginning 1.1 inches from the leading edge of the M/R blade to 4.9 
inches from the leading edge of the M/R blade should be revised to M/R 
blade stations 185.75 and 192.75, or measured from the tip end of the 
M/R blade between 36.25 inches and 29.25 inches beginning 1.2 inches 
from the leading edge of the M/R blade to 5.0 inches from the leading 
edge of the M/R blade. ``Zone 2'' described in the NPRM as M/R blade 
stations 186.0 and 191.0 should be revised to M/R blade stations 185.9 
and 192.9, or measured from the tip end of the M/R blade between 36.1 
inches and 29.1 inches.
    The FAA agrees and has revised this AD accordingly.

Request for a Change to the Service Bulletin Cited in Note 1

    Van Horn proposed that Note 1 to paragraph (g)(2)(i) cite Van Horn 
Service Bulletin Notice No. 33000-4R4, dated March 31, 2022 (SB33000-
4R4) rather than Van Horn Service Bulletin Notice No. 33000-4R3, dated 
November 8, 2021 (SB 33000-4R3).
    The FAA partially agrees. The FAA appreciates that the latest 
revision of that service bulletin is SB33000-4R4; however, the portions 
of that service bulletin that are specified in the proposed AD are 
identical in SB33000-4R3 and SB33000-4R4. Accordingly, the FAA has made 
updates throughout the Required Actions paragraph to allow both 
SB33000-4R3 and SB33000-4R4 in this final rule.

Request for a Reference to Additional Service Information in Note 1

    Van Horn proposed edits in Note 1 to paragraph (g)(2)(i) to refer 
to the Van Horn Instructions for Continued Airworthiness, ICA Manual 
No. VMM-MR-206L-501, Revision N/C, dated May 24, 2018, for a blade 
configuration drawing.
    The FAA disagrees because it does not provide information that 
could be helpful for operators to comply with this AD.

Request for Additional Tap Hammer Tool

    Van Horn also requested the FAA revise the list of tap hammers in 
paragraph (g)(2)(iii) of the proposed AD to add Van Horn Aviation Tap 
Hammer P/N VHACS0003 to the list of tap hammers.
    The FAA agrees and has revised this AD as requested.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, and determined that air safety requires adopting this AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these products. Except for minor editorial changes, and 
any other changes described previously, this AD is adopted as proposed 
in the NPRM. None of the changes will increase the economic burden on 
any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed SB 33000-4R3 and SB 33000-4R4. This service 
information specifies procedures to identify ``Zone 1'' and ``Zone 2'' 
inspection areas, accomplish repetitive visual and tap inspections of 
the zones to detect and monitor the growth of any delamination, and 
depending on the results, remove the M/R blade from service and contact 
Van Horn. SB 33000-4R3 applies to M/R blade P/N 20633000-101 serial 
numbers A012 through A104. SB 33000-4R4 expanded the applicability to 
include M/R blade P/N 20633000-101 with serial numbers A007, A008, and 
A009; these serial-numbered parts were included in the NPRM's 
applicability.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Differences Between This AD and the Service Information

    This AD requires using certain part-numbered composite tap hammers, 
whereas SB 33000-4R3 and SB 33000-4R4 do not. SB 33000-4R3 and SB 
33000-4R4 specify procedures to visually inspect the M/R blade, whereas 
this AD does not. If there is any delamination in the upper surface 
inspection zone (``Zone 1''), this AD requires removing the M/R blade 
from service, whereas SB 33000-4R3 and SB 33000-4R4 do not specify 
procedures for this condition.

Interim Action

    The FAA considers this AD to be an interim action. The inspection 
reports that are required by this AD will enable the FAA to obtain 
better insight into the unsafe condition. If final action is later 
identified, the FAA might consider further rulemaking.

Costs of Compliance

    The FAA estimates that this AD will affect 23 helicopters of U.S. 
registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this AD.
    Removing, tap inspecting, and re-installing an M/R blade will take 
about

[[Page 69163]]

4.5 work-hours for an estimated cost of $383 per M/R blade, per 
inspection cycle and up to $8,809 for the U.S. fleet per M/R blade, per 
inspection cycle. Replacing an M/R blade will take about 4 work-hours 
and parts will cost about $71,500 per M/R blade for a total of $71,840 
per M/R blade. Reporting information to Van Horn will take about 1 
work-hour for an estimated cost of $85 per report.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a currently valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to take 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, and completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Send comments regarding this burden estimate 
or any other aspect of this collection of information, including 
suggestions for reducing this burden to: Information Collection 
Clearance Officer, Federal Aviation Administration, 10101 Hillwood 
Parkway, Fort Worth, TX 76177-1524.

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

    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) 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.

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:

2022-22-08 Bell Textron Canada Limited (Type Certificate Previously 
Held by Bell Helicopter Textron Canada Limited): Amendment 39-22223; 
Docket No. FAA-2022-0286; Project Identifier AD-2021-01081-R.

(a) Effective Date

    This airworthiness directive (AD) is effective December 23, 
2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bell Textron Canada Limited (type certificate 
previously held by Bell Helicopter Textron Canada Limited) Model 
206L, 206L-1, 206L-3, and 206L-4 helicopters, certificated in any 
category, with main rotor (M/R) blade part number (P/N) 20633000-101 
with serial number A007, A008, A009, or A012 through A104 inclusive, 
installed under Supplemental Type Certificate SR02684LA.

(d) Subject

    Joint Aircraft System Component (JASC) Code: 6210, Main Rotor 
Blades.

(e) Unsafe Condition

    This AD was prompted by reports of delamination of M/R blades. 
The FAA is issuing this AD to address delamination of an M/R blade 
initiating in the 90[deg] plies at the lower inboard end of the 
weight pocket receptacle. The unsafe condition, if not addressed, 
could result in reduced structural integrity of the M/R blade, 
excessive vibration, and subsequent loss of control of the 
helicopter.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Accomplish the actions required by paragraph (g)(2) of this 
AD at the following compliance time, whichever occurs later:
    (i) Before the M/R blade accumulates 400 total hours time-in-
service (TIS) or 2,400 engine starts since initial installation on 
any helicopter, whichever occurs first; or
    (ii) Within 100 hours TIS after the effective date of this AD.
    (2) Remove each M/R blade from the helicopter, place it on a 
flat, stable surface, and accomplish the following:
    (i) Use a permanent marker to draw rectangular inspection ``Zone 
1'' on the upper surface of the M/R blade at M/R blade stations 
185.75 and 192.75, or measured from the tip end of the M/R blade 
between 36.25 inches and 29.25 inches, beginning 1.2 inches from the 
leading edge of the M/R blade to 5.0 inches from the leading edge of 
the M/R blade. Draw lines from the inboard end to the outboard end 
to connect each end at 1.2 inches and 5.0 inches. Draw parallel 
lines from the inboard end of the inspection zone to the outboard 
end of the inspection zone, with the lines spaced 0.50 inch apart.

    Note 1 to paragraph (g)(2)(i): This note applies to paragraphs 
(g)(2)(i) and (ii) of this AD. Figure 4 of Van Horn Aviation, LLC, 
Service Bulletin Notice No. 33000-4R3, dated November 8, 2021 (SB 
33000-4R3), and Van Horn Aviation, LLC, Service Bulletin Notice No. 
33000-4R4, dated March 31, 2022 (SB 33000-4R4) depict ``Zone 1'' and 
``Zone 2.''

    (ii) Use a permanent marker to draw rectangular inspection 
``Zone 2'' on the lower surface of the M/R blade at M/R blade 
stations 185.9 and 192.9, or measured from the tip end of the M/R 
blade between 36.1inches and 29.1 inches, beginning from the forward 
edge of the weight receptacle pocket and extending 1 inch in the 
direction towards the leading edge of the M/R blade. Draw lines from 
the inboard end to the outboard end to connect each end at the 
weight receptacle pocket and 1 inch forward of the weight receptacle 
pocket. Draw parallel lines from the inboard end of the inspection 
zone to the outboard end of the inspection zone, with the lines 
spaced 0.50 inch apart.
    (iii) Using composite tap hammer Abaris Training Tap Hammer P/N 
ABATH, HeatCon

[[Page 69164]]

Tap Hammer P/N HCS1104-01, Brown Tool Composite Tap Hammer P/N BAT-
CTH8, MATCO Tools Composite Tap Hammer P/N T4BAT-CTH8, or Van Horn 
Aviation Tap Hammer P/N VHACS0003, tap inspect the areas within 
``Zone 1'' and ``Zone 2'' for any delamination by following Tap 
Inspect Balance Receptacle, paragraph A.(4) of SB 33000-4R3 or SB 
33000-4R4. Where SB 33000-4R3 and SB 33000-4R4 specify to mark the 
location where the delamination starts, use a permanent marker.
    (iv) If there are any marks where the delamination starts, 
connect the marks indicating the delamination location and measure 
the length at the farthest point from the inboard end of the 
inspection area.
    (v) If there is any delamination in the lower surface inspection 
zone (``Zone 2'') that is 6.0 or more inches in length or if there 
is any delamination in the upper surface inspection zone (``Zone 
1''), before further flight, remove the M/R blade from service.
    (3) Thereafter repeat the actions required by paragraph (g)(2) 
of this AD at intervals not to exceed 400 hours TIS or 2,400 engine 
starts, whichever occurs first.
    (4) If there is any delamination, within 30 days after 
accomplishing the actions required by paragraphs (g)(1) or (3) of 
this AD, report each delamination size and location, and the total 
hours TIS and total engine starts since initial installation of the 
M/R blade, to Mr. Dean Rosenlof, Van Horn Aviation, LLC, 1510 West 
Drake Drive, Tempe, AZ 85283, or by email to 
[email protected].

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of 
the person identified in paragraph (i) of this AD. Information may 
be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(i) Related Information

    For more information about this AD, contact Payman Soltani, 
Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, 
Compliance & Airworthiness Division, FAA, 3960 Paramount Blvd., 
Lakewood, CA 90712; telephone (562) 627-5313; email 
[email protected].

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Van Horn Aviation, LLC, Service Bulletin Notice No. 33000-
4R3, dated November 8, 2021.
    (ii) Van Horn Aviation, LLC, Service Bulletin Notice No. 33000-
4R4, dated March 31, 2022.
    (3) For Van Horn Aviation, LLC, service information identified 
in this AD, contact Dean Rosenlof, Van Horn Aviation, LLC, 1510 West 
Drake Drive, Tempe, AZ, 85283, United States; phone: (480) 483-4202; 
email: [email protected].
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on October 21, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-25030 Filed 11-17-22; 8:45 am]
BILLING CODE 4910-13-P


