Rule2021-12229
Airworthiness Directives; Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited) Helicopters
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
June 11, 2021
Effective
July 16, 2021
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) (Bell) Model 505 helicopters. This AD was prompted by the discovery of a gap between the transmission restraint assembly aft attachment hardware lower washer and mating airframe truss assembly (truss assembly) clevis lower lug. This AD requires inspecting the transmission restraint aft attachment hardware installation for a gap and corrective action depending on the inspection results. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 86 Issue 111 (Friday, June 11, 2021)</title>
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[Federal Register Volume 86, Number 111 (Friday, June 11, 2021)]
[Rules and Regulations]
[Pages 31089-31092]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-12229]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0185; Project Identifier MCAI-2020-00265-R;
Amendment 39-21581; AD 2021-11-19]
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) (Bell) Model 505 helicopters. This
AD was prompted by the discovery of a gap between the transmission
restraint assembly aft attachment hardware lower washer and mating
airframe truss assembly (truss assembly) clevis lower lug. This AD
requires inspecting the transmission restraint aft attachment hardware
installation for a gap and corrective action depending on the
inspection results. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 16, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of July 16, 2021.
ADDRESSES: For service information identified in this final rule,
contact Bell Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel,
Quebec J7J1R4; telephone 450-437-2862 or 800-363-8023; fax 450-433-
0272; or at <a href="https://www.bellcustomer.com">https://www.bellcustomer.com</a>. You may view the referenced
service information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX
76177. Service information that is incorporated by reference is also
available at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating
Docket No. FAA-2021-0185.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2021-0185; 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, the
Transport Canada AD, any comments received, and other information. The
street 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: Matt Fuller, AD Program Manager,
General Aviation & Rotorcraft Unit, Airworthiness Products Section,
Operational Safety Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817-222-5110; email <a href="/cdn-cgi/l/email-protection#c5a8a4b1b1ada0b2eba3b0a9a9a0b785a3a4a4eba2aab3"><span class="__cf_email__" data-cfemail="d6bbb7a2a2beb3a1f8b0a3babab3a496b0b7b7f8b1b9a0">[email protected]</span></a>.
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 Model 505
helicopters with a truss assembly part number (P/N) SLS-030-056-015
with a serial number (S/N) listed in Attachment A of Bell Alert Service
Bulletin (ASB) 505-19-12, Revision A, dated July 11, 2019 (505-19-12
Rev A). The NPRM published in the Federal Register on March 22, 2021
(86 FR 15146). In the NPRM, the FAA proposed to require the following
within 100 hours time-in-service (TIS):
<bullet> Accessing and cleaning the lower attachment hardware
securing the restraint to the truss assembly, loosening the torque on
each lower nut to measure the tare, and adding a torque value of 20
inch-lbs to the measured tare of each nut and torqueing each nut to
this new total value.
<bullet> Inspecting for a gap around the circumference between the
nut and the washer and between the washer and the truss assembly clevis
lower lug mounting surface of the right-hand (RH) and left-hand (LH)
sides, and if there is a gap, measuring the gap.
<bullet> If there is a gap that is less than 0.003 inch (0.076 mm),
installing the hardware using the original torque value of 40 to 58
foot-pounds (55 to 78 Nm) plus tare and completing the installation of
the attachment point.
<bullet> If there is a gap that is 0.003 inch (0.076 mm) to 0.020
inch (0.508 mm) inclusive, installing the hardware with a decreased
torque value limit of 20 to 60 inch-pounds (2.3 to 6.8 Nm) plus tare
and completing the installation of the attachment point. The NPRM also
proposed to require updating records for your helicopter to indicate
the new torque limits on one or both sides. Thereafter, within 100
hours TIS, and thereafter at intervals not to exceed 100 hours TIS, the
NPRM proposed to
[[Page 31090]]
require inspecting the assembly for fretting between the washer and
truss lower lug mounting surface, the security of the pitch restraint
attachment hardware to make sure it does not turn freely, and the
torque seal lacquer between the nut and the washer to make sure the
torque seal is intact on the RH and LH sides. Depending on the
inspection results, the NPRM proposed to require removing the cotter
pin from service and removing the nut, washer, and bolt, and inspecting
the bolt and the lower surface of the truss assembly clevis lower lug.
Depending on these inspection results, the NPRM proposed to require
removing the bolt from service; reworking and cleaning the lower
surface of the clevis lower lug and inspecting for any cracks; removing
the clevis lower lug from service; or applying primer and final paint.
The NPRM then proposed to require installing the hardware with a
decreased torque value limit of 20 to 60 inch-pounds (2.3 to 6.8 Nm)
plus tare and completing the installation of the attachment point.
<bullet> If there is a gap that is more than more than 0.020 inch
(0.508 mm), removing the nut, washer, and bolt from service and
repairing or replacing the truss assembly clevis lower lug in
accordance with FAA-approved procedures.
The NPRM was prompted by Canadian AD CF-2019-35, dated October 2,
2019 (Transport Canada AD CF-2019-35), issued by Transport Canada,
which is the aviation authority for Canada, to correct an unsafe
condition for Bell Model 505 helicopters, S/Ns 65011 and subsequent.
Transport Canada advises of a gap between the transmission restraint
assembly aft attachment hardware lower washer and the lower lug of the
truss assembly clevis identified during quality control activity of a
helicopter in final assembly. This gap can occur on the RH and LH sides
of the truss assembly clevis. Subsequent investigation revealed that
this condition may exist on in-service helicopters. Transport Canada
advises that excessive gapping at either of these locations will result
in increased stress when fasteners are installed and that the increased
stress may result in cracking on the clevis lower lug and subsequent
failure of one or both clevis lower lugs. Transport Canada further
advises that this condition, if not corrected, could lead to loss of
pylon pitch stiffness, excessive pylon pitch motions leading to unknown
cyclic inputs to the main rotor, and consequent loss of control of the
helicopter.
Accordingly, Transport Canada AD CF-2019-35 requires identifying
the S/N of the installed truss assembly, and for a helicopter with an
affected truss assembly installed, performing an initial inspection of
the transmission restraint aft attachment hardware installations for a
gap. Depending on the inspection results, Transport Canada AD CF-2019-
35 requires reducing the torque to the attachment hardware, updating
records, and repetitive inspections of the attachment hardware for wear
and fretting because of the reduced friction between the mating
surfaces; reporting findings to Bell and accomplishing corrective
actions specified by Bell; or completing the installation of the
attachment hardware and updating records.
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
These helicopters have been approved by the aviation authority of
Canada and are approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with Canada, Transport Canada, its
technical representative, has notified the FAA of the unsafe condition
described in its AD. The FAA reviewed the relevant data 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
helicopters.
Related Service Information Under 1 CFR Part 51
The FAA reviewed 505-19-12 Rev A. This service information
specifies procedures for an inspection of the restraint hardware
installation for the presence of a gap and if needed, reducing the
torque to the affected attachment hardware, a repetitive 100-hour
inspection of the pitch restraint attachment hardware, and repair of
fretting damage on the truss assembly clevis lower lug.
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.
Other Related Service Information
The FAA also reviewed Bell ASB 505-19-12, dated June 27, 2019. This
original version of the service information contains the same
procedures as 505-19-12 Rev A, except 505-19-12 Rev A corrects a torque
value.
Differences Between This AD and the Transport Canada AD
The applicability of the Transport Canada AD is by helicopter S/N
and requires identifying the S/N of the installed truss assembly P/N
SLS-030-056-015 to determine if the helicopter is affected by the
unsafe condition, whereas the applicability of this AD is by
helicopters with certain serial-numbered truss assembly P/N SLS-030-
056-015 installed instead. The compliance time of the initial
inspections required by the Transport Canada AD is within 100 hours air
time or 6 months, whichever occurs first, whereas the compliance time
in this AD is within 100 hours TIS. The Transport Canada AD requires
reporting information to Bell to obtain certain corrective action,
while this AD requires repairing or removing affected parts from
service instead.
Costs of Compliance
The FAA estimates that this AD affects 87 helicopters of U.S.
registry. Labor costs are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
Measuring tare and inspecting for a gap between the transmission
restraint assembly aft attachment hardware lower washer and the truss
assembly will take about 1 work-hour for an estimated cost of $85 per
helicopter and $7,395 for the U.S. fleet. If required, inspecting a
pitch restraint attachment point will take about 1 work-hour for an
estimated cost of $85 per attachment point per inspection cycle.
The FAA estimates the following costs to do any necessary repairs
or replacements based on the results of the inspections:
<bullet> Updating records to indicate the new torque limits will
take about 0.25 work-hour for an estimated cost of $21.
<bullet> Replacing a bolt will take a minimal additional amount of
time after inspecting and the part will cost about $50.
<bullet> Reworking the lower surface of the clevis lower lug will
take about 1 work-hour for an estimated cost of $85.
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
[[Page 31091]]
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 helicopters 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:
2021-11-19 Bell Textron Canada Limited (Type Certificate Previously
Held by Bell Helicopter Textron Canada Limited): Amendment 39-21581;
Docket No. FAA-2021-0185; Project Identifier MCAI-2020-00265-R.
(a) Effective Date
This airworthiness directive (AD) is effective July 16, 2021.
(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 505
helicopters, certificated in any category, with a truss assembly
part number (P/N) SLS-030-056-015 with a serial number listed in
Attachment A of Bell Alert Service Bulletin (ASB) 505-19-12,
Revision A, dated July 11, 2019 (ASB 505-19-12 Rev A).
(d) Subject
Joint Aircraft System Component (JASC) Code 5310, Fuselage Main,
Structure.
(e) Unsafe Condition
The FAA is issuing this AD to address a gap between the
transmission restraint assembly aft attachment hardware lower washer
and the right-hand (RH) and left-hand (LH) mating airframe truss
assembly (truss assembly) clevis lower lug. The unsafe condition, if
not addressed, could result in increased stress, cracking and
failure of one or both of the clevis lower lugs, and subsequent loss
of pylon pitch stiffness, excessive pylon pitch motions leading to
unknown cyclic inputs to the main rotor, and loss of control of the
helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within 100 hours time-in-service (TIS) after the effective date
of this AD, access the transmission restraint assembly and:
(1) Remove the safety pin at each lower nut location of the aft
bolts securing the restraint to the truss assembly. Use solvent (C-
304) to remove the corrosion preventive compound on each nut and
washer located under the RH and LH truss assembly clevis lower lug.
(2) Loosen the torque on each lower nut while holding the bolt
with a wrench until the washer turns freely while sitting on top of
the nut.
(3) Measure and record the tare of each nut. For purposes of
this AD, tare is the torque required to overcome the internal
friction between a self-locking nut and bolt as the nut is being
turned on the bolt, but before the nut contacts the washer. Add a
torque value of 20 inch-lbs to the measured tare of each nut and
torque each nut to this new total value.
(4) Inspect for a gap around the circumference between the nut
and the washer and between the washer and the truss assembly clevis
lower lug mounting surface of the RH and LH sides as illustrated in
Figure 1 of ASB 505-19-12 Rev A (2 sheets). If there is a gap,
measure the gap.
(i) If there is a gap that is less than 0.003 inch (0.076 mm),
before further flight, install the hardware using the original
torque value of 40 to 58 foot-pounds (55 to 78 Nm) plus tare. Do not
exceed the limit specified in this paragraph plus tare. Install a
cotter pin and apply corrosion preventive compound (C-101) and
torque seal lacquer (C-049) between the nut, washer, and lower
surface of the truss assembly clevis.
(ii) If there is a gap that is 0.003 inch (0.076 mm) to 0.020
inch (0.508 mm) inclusive, before further flight, install the
hardware with a decreased torque value limit of 20 to 60 inch-pounds
(2.3 to 6.8 Nm) plus tare. Do not exceed the limit specified in this
paragraph plus tare. Install a cotter pin. You may install an
additional washer P/N NAS1149E0863P before torqueing and installing
the cotter pin while not exceeding the maximum limit of 60 inch-lbs
plus tare. Apply corrosion preventive compound (C-101) and torque
seal lacquer (C-049) between the nut, washer, and lower surface of
the truss assembly clevis. Update records for your helicopter to
indicate the new torque limits on one or both sides.
(A) Within 100 hours TIS after performing paragraph (g)(4)(ii)
of this AD, and thereafter at intervals not to exceed 100 hours TIS,
inspect the assembly for fretting between the washer and truss lower
lug mounting surface, inspect the security of the pitch restraint
attachment hardware to make sure it does not turn freely, and
inspect the torque seal lacquer between the nut and the washer to
make sure the torque seal is intact on the RH and LH sides.
(B) If there is any fretting, the pitch restraint attachment
hardware turns freely, or a torque seal is broken, remove the cotter
pin from service and remove the nut, washer, and bolt. Inspect the
bolt for damage and the lower surface of the truss assembly clevis
lower lug for fretting damage.
(1) If the bolt has damage, remove the bolt from service.
(2) If the lower surface of the truss assembly clevis lower lug
has fretting damage within allowable repair limits, use 400 grit
sandpaper (C-423) and rework fretting damage smooth with adjacent
surfaces, while removing minimum material. Do not exceed .010 inch
(0.254 mm) deep total cumulative amount of material to be removed
from the clevis's lower lugs compared to adjacent original surfaces
after rework. Clean with acetone (C-316) and let dry. With the
acetone dry, visually inspect the clevis lower lug for any cracks.
(i) If there is a crack within allowable repair limits, repair
in accordance with FAA-approved procedures. If there is a crack that
meets or exceeds allowable repair limits, remove the truss assembly
clevis lower lug from service.
(ii) If there is not a crack, apply primer (C-204) to the
reworked surface and let dry. With the primer dry, apply final paint
(polyurethane topcoat color No. 16492) to the reworked surface.
(3) If the lower surface of the truss assembly clevis lower lug
has fretting damage that exceeds allowable repair limits, before
further flight, remove the truss assembly clevis lower lug from
service.
(C) Install a nut, washer, and bolt with a decreased torque
value limit of 20 to 60 inch-pounds (2.3 to 6.8 Nm) plus tare. Do
not exceed the limit specified in this paragraph plus tare. Install
a cotter pin. You may install an additional washer P/N NAS1149E0863P
before torqueing and installing the cotter pin while not exceeding
the maximum limit of 60 inch-lbs plus tare. Apply corrosion
preventive compound (C-101) and torque seal lacquer (C-049) between
the nut, washer, and lower surface of the truss assembly clevis.
[[Page 31092]]
(iii) If there is a gap that is more than 0.020 inch (0.508 mm),
before further flight, remove the nut, washer, and bolt from service
and repair or replace the truss assembly clevis lower lug in
accordance with FAA-approved procedures.
(h) Credit for Previous Actions
You may take credit for the first instance of the actions that
are required by paragraphs (g)(1) through (4) of this AD, except not
paragraphs (g)(4)(i), (g)(4)(ii)(A) through (C), or (g)(4)(iii) of
this AD if you completed the Accomplishment Instructions, Part I of
Bell ASB 505-19-12, dated June 27, 2019, before the effective date
of this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, International Validation 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 International Validation Branch, send
it to the attention of the person identified in paragraph (j)(1) of
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#b0899df1e6e39df1f9e29d8783809df1fdfff3f0d6d1d19ed7dfc6"><span class="__cf_email__" data-cfemail="bf8692fee9ec92fef6ed92888c8f92fef2f0fcffd9dede91d8d0c9">[email protected]</span></a>.
(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.
(j) Related Information
(1) For more information about this AD, contact Matt Fuller, AD
Program Manager, General Aviation & Rotorcraft Unit, Airworthiness
Products Section, Operational Safety Branch, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; email
<a href="/cdn-cgi/l/email-protection#dcb1bda8a8b4b9abf2baa9b0b0b9ae9cbabdbdf2bbb3aa"><span class="__cf_email__" data-cfemail="3b565a4f4f535e4c155d4e57575e497b5d5a5a155c544d">[email protected]</span></a>.
(2) Bell Alert Service Bulletin 505-19-12, dated June 27, 2019,
which is not incorporated by reference, contains additional
information about the subject of this AD. This service information
is available at the contact information specified in paragraphs
(k)(3) and (4) of this AD.
(3) The subject of this AD is addressed in Transport Canada AD
CF-2019-35, dated October 2, 2019. You may view the Transport Canada
AD at <a href="https://www.regulations.gov">https://www.regulations.gov</a> in Docket No. FAA-2021-0185.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference 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) Bell Alert Service Bulletin 505-19-12, Revision A, dated
July 11, 2019.
(ii) [Reserved]
(3) For service information identified in this AD, contact Bell
Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec
J7J1R4; telephone 450-437-2862 or 800-363-8023; fax 450-433-0272; or
at <a href="https://www.bellcustomer.com">https://www.bellcustomer.com</a>.
(4) 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.
(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: <a href="/cdn-cgi/l/email-protection#3f595a5b4d5a5811535a585e537f515e4d5e11585049"><span class="__cf_email__" data-cfemail="17717273657270397b7270767b577976657639707861">[email protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on May 20, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-12229 Filed 6-10-21; 8:45 am]
BILLING CODE 4910-13-P
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This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.