[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 [www.gpo.gov]
[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 regulations.gov 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:
     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 
[email protected]; or at bellflight.com/support/contact-support.
     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 
regulations.gov 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: [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 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 
regulations.gov 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: [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. 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: 
[email protected].

(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: [email protected].
    (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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    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