Rule2024-15808
Airworthiness Directives; Bell 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
July 18, 2024
Effective
August 22, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 407 helicopters. This AD was prompted by a report that a certain part-numbered fuel system standpipe assembly (standpipe) may have sharp edges at the interval weld joints due to a quality escape during the manufacturing process. This AD requires inspecting certain fuel system parts and, depending on the inspection results, taking corrective actions and performing a fuel quantity gauging system calibration. Depending on the results of the fuel quantity gauging system calibration, this AD requires performing additional corrective actions and repeating the fuel quantity gauging system calibration. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 89 Issue 138 (Thursday, July 18, 2024)</title>
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[Federal Register Volume 89, Number 138 (Thursday, July 18, 2024)]
[Rules and Regulations]
[Pages 58260-58262]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-15808]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0232; Project Identifier MCAI-2023-00353-R;
Amendment 39-22758; AD 2024-10-12]
RIN 2120-AA64
Airworthiness Directives; Bell 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
certain Bell Textron Canada Limited Model 407 helicopters. This AD was
prompted by a report that a certain part-numbered fuel system standpipe
assembly (standpipe) may have sharp edges at the interval weld joints
due to a quality escape during the manufacturing process. This AD
requires inspecting certain fuel system parts and, depending on the
inspection results, taking corrective actions and performing a fuel
quantity gauging system calibration. Depending on the results of the
fuel quantity gauging system calibration, this AD requires performing
additional corrective actions and repeating the fuel quantity gauging
system calibration. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 22, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 22,
2024.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-0232; 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.
Material Incorporated by Reference:
<bullet> For Bell material, contact Bell Textron Canada Limited,
12,800 Rue de l'Avenir, Mirabel, Quebec J7J 1R4, Canada; phone 1-450-
437-2862 or 1-800-363-8023; fax 1-450-433-0272; email
<a href="/cdn-cgi/l/email-protection#bacac8d5decfd9cec9cfcacad5c8cefad8dfd6d6dcd6d3ddd2ce94d9d5d7"><span class="__cf_email__" data-cfemail="8efefce1eafbedfafdfbfefee1fcfaceecebe2e2e8e2e7e9e6faa0ede1e3">[email protected]</span></a>; or at <a href="http://bellflight.com/support/contact-support">bellflight.com/support/contact-support</a>.
<bullet> You may view this material 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
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2024-0232.
FOR FURTHER INFORMATION CONTACT: Michael Hughlett, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
phone: (817) 222-5889; email: <a href="/cdn-cgi/l/email-protection#a2cfcbc1cac3c7ce8cead7c5cacec7d6d6e2c4c3c38cc5cdd4"><span class="__cf_email__" data-cfemail="25484c464d4440490b6d50424d49405151654344440b424a53">[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 Textron Canada
Limited Model 407 helicopters, serial numbers 54832 through 54931
inclusive, 54933 through 54939 inclusive, and 54942 through 54954
inclusive, with a certain part-numbered fuel system standpipe assembly
installed. The NPRM published in the Federal Register on February 20,
2024 (89 FR 12792). The NPRM was prompted by Transport Canada AD CF-
2023-11, dated February 23, 2023 (Transport Canada AD CF-2023-11),
issued by Transport Canada, which is the aviation authority for Canada.
Transport Canada AD CF-2023-11 states that, due to a quality escape,
standpipe part number (P/N) 407-062-032-103 may have been delivered
with sharp edges at the internal weld joints.
In the NPRM, the FAA proposed to require, with the standpipe
removed, inspecting its interior for any sharp edges on each internal
weld joint. If there are any sharp edges on any weld joint, the NPRM
proposed to require deburring the edges, ensuring not to exceed a
certain depth into the tube. The NPRM then proposed to require removing
all sanding residue and applying a chemical film to any bare metal
surfaces. The NPRM also proposed to require, with the harness assembly
removed, inspecting the harness assembly connectors for any mechanical
damage and corrosion to the electrical pins, and inspecting the
insulation tubing and wires of the harness assembly for any crack and
chafing. Depending on these results, the NPRM proposed to require
replacing the harness assembly.
If the harness assembly was required to be replaced as a result of
the proposed AD requirements, the NPRM proposed to require performing a
fuel quantity gauging system calibration.
[[Page 58261]]
Depending on the calibration results, the NPRM proposed to require
replacing the harness assembly and repeating the fuel quantity gauging
system calibration. The FAA is issuing this AD to address the unsafe
condition on these products.
You may examine the Transport Canada AD in the AD docket at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2024-0232.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
These helicopters have been approved by Transport Canada and are
approved for operation in the United States. Pursuant to the FAA's
bilateral agreement with Canada, Transport Canada has notified the FAA
about the unsafe condition described in its AD. Except for minor
editorial changes, this AD is adopted as proposed in the NPRM.
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 Bell Alert Service Bulletin 407-21-124, dated
February 1, 2022, which specifies procedures for a one-time visual
inspection of the internal weld joints of standpipe P/N 407-062-032-
103. If there are any sharp edges, this service information specifies
rework procedures, which include deburring the sharp edges, removing
all residue, and applying a chemical film. This service information
also specifies procedures to remove and inspect the harness assembly
connectors for any damage to the electrical pins and inspect the
insulation tubing and wires for any cracks and chafing.
Additionally, this service information specifies if any damage is
found, contacting product support engineering and submitting certain
information. Finally, this service information specifies instructions
for various fuel procedures and checks.
The FAA also reviewed Fuel Quantity Gauging System, DMC-407-A-95-
65-10-01A-273A-A, dated June 2, 2022, of Chapter 95--Instruments, of
Bell Model 407 Maintenance Manual, BHT-407-MM, Issue No. 014, dated
December 12, 2023, which specifies procedures for a fuel quantity
gauging system calibration procedure and inspecting the fuel quantity
display information.
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in ADDRESSES.
Differences Between This AD and the Transport Canada AD
Transport Canada AD CF-2023-11 requires contacting Bell for
disposition instructions if damage is found on the harness assembly,
whereas this AD requires removing an affected harness assembly from
service and replacing it with an airworthy harness assembly.
Costs of Compliance
The FAA estimates that this AD affects 51 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.
Inspecting the interior of the standpipe will take approximately 1
work-hour for an estimated cost of $85 per helicopter and $4,335 for
the U.S. fleet.
Inspecting the harness assembly connectors, insulation tubing, and
wiring will take approximately 1 work-hour for an estimated cost of $85
per helicopter and $4,335 for the U.S. fleet.
If required, deburring, cleaning, and applying a chemical film to
each affected weld joint will take approximately 0.5 work-hour for an
estimated cost of $43 per weld joint.
If required, replacing an affected harness assembly will take
approximately 1 work-hour and parts will cost approximately $1,071 for
an estimated cost of $1,156 per harness replacement.
If required, performing a fuel quantity gauging system calibration
will take approximately 10 work-hours for an estimated cost of $850 per
procedure.
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.
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:
2024-10-12 Bell Helicopter Textron Canada Limited: Amendment 39-
22758; Docket No. FAA-2024-0232; Project Identifier MCAI-2023-00353-
R.
(a) Effective Date
This airworthiness directive (AD) is effective August 22, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Canada Limited Model 407
helicopters, serial numbers 54832 through 54931 inclusive, 54933
through 54939 inclusive, and 54942 through 54954 inclusive,
certificated in any
[[Page 58262]]
category, with a fuel system standpipe assembly (standpipe) part
number 407-062-032-103 installed.
(d) Subject
Joint Aircraft System Component (JASC) Code: 2897, Fuel system
wiring.
(e) Unsafe Condition
This AD was prompted by a report that certain standpipes may
have sharp edges at the interval weld joints due to a quality escape
during the manufacturing process. The FAA is issuing this AD to
detect sharp edges in the standpipe. The unsafe condition, if not
addressed, could result in fuel quantity system wiring damage, loss
of or erratic fuel quantity indication.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
(1) Within 300 hours time-in-service (TIS) or 6 months after the
effective date of this AD, whichever occurs first, accomplish the
actions required by paragraphs (g)(1)(i) and (ii) of this AD.
(i) With the standpipe removed from the aft fuel cell, inspect
the interior of the standpipe for any sharp edges on each internal
weld joint, as shown in Figure 1 of Bell Alert Service Bulletin 407-
21-124, dated February 1, 2022. If there is a sharp edge on any
internal weld joint, before further flight, deburr the edges of each
affected weld joint using an aluminum oxide abrasive cloth or paper,
or equivalent, ensuring not to exceed 0.015 in (0.38 mm) depth into
the tube material at a 45-degree angle to the weld joint. Then,
using a clean cloth dampened with isopropyl alcohol or equivalent,
remove all sanding residue from the weld joint and apply a chemical
film material to any bare metal surfaces.
(ii) With the fuel quantity harness assembly (harness assembly)
removed, inspect the harness assembly connectors for any mechanical
damage and corrosion to the electrical pins and inspect the
insulation tubing and wires for any cracks and chafing. For the
purposes of this AD, mechanical damage is indicated by deterioration
of the connections or pins.
(A) If there is any corrosion or mechanical damage, before
further flight, remove the harness assembly from service and replace
it with an airworthy harness assembly.
(B) If there is a crack or any chafing, before further flight,
remove the harness assembly from service and replace it with an
airworthy harness assembly.
(2) If the harness assembly was required to be replaced as a
result of the inspection required by paragraph (g)(1)(ii) of this AD
or by this paragraph, before further flight, with the standpipe and
harness assembly installed, perform a fuel quantity gauging system
calibration in accordance with paragraphs 4 through 18 of Fuel
Quantity Gauging System, DMC-407-A-95-65-10-01A-273A-A, dated June
2, 2022, of Chapter 95--Instruments, of Bell Model 407 Maintenance
Manual, BHT-407-MM, Issue No. 014, dated December 12, 2023. As a
result of the fuel quantity gauging system calibration, if a fuel
level does not indicate the correct reading or displays no reading,
before further flight, remove the harness assembly from service and
replace it with an airworthy harness assembly; and repeat the
actions required by this paragraph for the newly installed harness
assembly.
(h) 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 (i) of
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#0d34204c5b5e204c445f203a3e3d204c40424e4d6b6c6c236a627b"><span class="__cf_email__" data-cfemail="a89185e9fefb85e9e1fa859f9b9885e9e5e7ebe8cec9c986cfc7de">[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. The following provisions also apply to this AD.
(i) Related Information
For more information about this AD, contact Michael Hughlett,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (817) 222-5889; email:
<a href="/cdn-cgi/l/email-protection#b2dfdbd1dad3d7de9cfac7d5daded7c6c6f2d4d3d39cd5ddc4"><span class="__cf_email__" data-cfemail="fb969298939a9e97d5b38e9c93979e8f8fbb9d9a9ad59c948d">[email protected]</span></a>.
(j) 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 407-21-124, dated February 1,
2022.
(ii) Fuel Quantity Gauging System, DMC-407-A-95-65-10-01A-273A-
A, dated June 2, 2022, of Chapter 95--Instruments, of Bell Model 407
Maintenance Manual, BHT-407-MM, Issue No. 014, dated December 12,
2023.
(3) For Bell Helicopter Textron Canada Limited material, contact
Grant Walker, 330 Sparks St., Ottawa, K1A 0N5, Canada; phone: (888)
663-3639; email: <a href="/cdn-cgi/l/email-protection#4720352629336930262b2c2235073324692024692426"><span class="__cf_email__" data-cfemail="482f3a29263c663f2924232d3a083c2b662f2b662b29">[email protected]</span></a>.
(4) You may view this material 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 material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#6107134f080f1211040215080e0f210f0013004f060e17"><span class="__cf_email__" data-cfemail="6d0b1f4304031e1d080e190402032d030c1f0c430a021b">[email protected]</span></a>.
Issued on July 10, 2024.
James D. Foltz,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-15808 Filed 7-17-24; 8:45 am]
BILLING CODE 4910-13-P
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