Proposed Rule2022-17140
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
August 15, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 99- 23-18, AD 2005-03-07, AD 2013-12-07, and AD 2014-04-07, which apply to certain Bell Helicopter Textron Canada (now Bell Textron Canada Limited) Model 407 helicopters. AD 99-23-18 requires revising the life limits for certain parts, replacing each part that has exceeded its life limit, and revising the Airworthiness Limitation Section (ALS) of the existing maintenance manual. AD 2005-03-07 requires establishing a maximum accumulated Retirement Index Number (RIN) count for certain crosstube assemblies and revising the ALS of the existing maintenance manual. AD 2013-12-07 requires inspecting the tailboom assembly for a crack, loose rivet, or other damage and depending on the inspection results, replacing certain parts. AD 2014-04-07 requires preflight checking, repetitively inspecting for a crack in certain tailbooms, modifying and re-identifying certain tailbooms, installing an improved horizontal stabilizer assembly, and revising the ALS of the existing maintenance manual. Since the FAA issued those ADs, a report was received of a crack on the tailboom lower skin due to fatigue damage and new and more restrictive airworthiness limitations have been issued. This proposed AD would require incorporating into existing maintenance records requirements (airworthiness limitations) as specified in the ALS service information. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 156 (Monday, August 15, 2022)</title>
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[Federal Register Volume 87, Number 156 (Monday, August 15, 2022)]
[Proposed Rules]
[Pages 50005-50009]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-17140]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 87, No. 156 / Monday, August 15, 2022 /
Proposed Rules
[[Page 50005]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0992; Project Identifier MCAI-2022-00173-R]
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: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 99-
23-18, AD 2005-03-07, AD 2013-12-07, and AD 2014-04-07, which apply to
certain Bell Helicopter Textron Canada (now Bell Textron Canada
Limited) Model 407 helicopters. AD 99-23-18 requires revising the life
limits for certain parts, replacing each part that has exceeded its
life limit, and revising the Airworthiness Limitation Section (ALS) of
the existing maintenance manual. AD 2005-03-07 requires establishing a
maximum accumulated Retirement Index Number (RIN) count for certain
crosstube assemblies and revising the ALS of the existing maintenance
manual. AD 2013-12-07 requires inspecting the tailboom assembly for a
crack, loose rivet, or other damage and depending on the inspection
results, replacing certain parts. AD 2014-04-07 requires preflight
checking, repetitively inspecting for a crack in certain tailbooms,
modifying and re-identifying certain tailbooms, installing an improved
horizontal stabilizer assembly, and revising the ALS of the existing
maintenance manual. Since the FAA issued those ADs, a report was
received of a crack on the tailboom lower skin due to fatigue damage
and new and more restrictive airworthiness limitations have been
issued. This proposed AD would require incorporating into existing
maintenance records requirements (airworthiness limitations) as
specified in the ALS service information. The FAA is proposing this AD
to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by September
29, 2022.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">www.regulations.gov</a>.
Follow the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays.
For service information that is identified in this NPRM, contact
Bell Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec
J7J 1R4, Canada; telephone 1-450-437-2862 or 1-800-363-8023; fax 1-450-
433-0272; email <a href="/cdn-cgi/l/email-protection#a4d4d6cbc0d1c7d0d7d1d4d4cbd6d0e4c6c1c8c8c2c8cdc3ccd08ac7cbc9"><span class="__cf_email__" data-cfemail="7b0b09141f0e180f080e0b0b14090f3b191e17171d17121c130f55181416">[email protected]</span></a>; or at
<a href="http://www.bellflight.com/support/contact-support">www.bellflight.com/support/contact-support</a>. 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.
Examining the AD Docket
You may examine the AD docket at <a href="http://www.regulations.gov">www.regulations.gov</a> by searching
for and locating Docket No. FAA-2022-0992; 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 NPRM, the Transport
Canada AD, any comments received, and other information. The street
address for Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer,
COS Program Management Section, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY
11590; telephone (516) 228-7330; email <a href="/cdn-cgi/l/email-protection#35545b514750541b5f5c58505b504f755354541b525a43"><span class="__cf_email__" data-cfemail="b3d2ddd7c1d6d29dd9daded6ddd6c9f3d5d2d29dd4dcc5">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2022-0992; Project Identifier
MCAI-2022-00173-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="http://www.regulations.gov">www.regulations.gov</a>, including any personal information you provide.
The agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Andrea Jimenez, Aerospace Engineer, COS Program Management Section,
Operational Safety Branch, Compliance & Airworthiness Division, FAA,
1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email <a href="/cdn-cgi/l/email-protection#1978777d6b7c78377370747c777c63597f7878377e766f"><span class="__cf_email__" data-cfemail="f7969993859296d99d9e9a9299928db7919696d9909881">[email protected]</span></a>. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.
[[Page 50006]]
Background
The FAA issued AD 99-23-18, Amendment 39-11414 (64 FR 61784,
November 15, 1999) (AD 99-23-18) for all Bell Helicopter Textron Canada
(now Bell Textron Canada Limited) Model 407 helicopters. AD 99-23-18
was prompted by an engineering evaluation of additional flight test
data, which resulted in redefining the service life for certain parts
and revising the ALS of the existing maintenance manual AD 99-23-18
requires before further flight, revising the life limits for certain
parts, and replacing each part that has exceeded its life limit with an
airworthy part. AD 99-23-18 also requires revising the ALS of the
existing maintenance manual to reflect these new life limits and
annotating the component history card or equivalent record with the
revised life limits.
The FAA issued AD 2005-03-07, Amendment 39-13963 (70 FR 7016,
February 10, 2005) (AD 2005-03-07) for Bell Helicopter Textron Canada
(now Bell Textron Canada Limited) Model 407 helicopters with landing
gear crosstube assemblies, part number (P/N) 407-050-101-101 and -103;
P/N 407-050-102-101 and -103; P/N 407-050-201-101 and -103; P/N 407-
050-202-101 and -103; P/N 407-704-007-119; P/N 407-722-101; P/N 407-
723-104; P/N 407-724-101; or P/N 407-725-104, installed. AD 2005-03-07
was prompted by fatigue testing, analysis, and evaluation by the
manufacturer that determined that run-on landings impose a high stress
on landing gear or crosstubes and may cause cracking in the area above
the skid tube saddle. AD 2005-03-07 requires before further flight,
establishing a component history card or equivalent record, converting
accumulated run-on landings to an accumulated RIN count, and
establishing a maximum accumulated RIN for certain crosstube
assemblies. AD 2005-03-07 also requires replacing any crosstube
assembly before it exceeds the maximum RIN life limit and revising the
ALS of the existing maintenance manual to reflect this new life limit.
The FAA issued AD 2013-12-07, Amendment 39-17485 (78 FR 38546, June
27, 2013) (AD 2013-12-07) for Bell Helicopter Textron Canada (now Bell
Textron Canada Limited) Model 407 helicopters with tailboom assembly P/
N 407-030-801-201, 407-030-801-203, or 407-030-801-205, installed. AD
2013-12-07 was prompted by a stress analysis of the tailboom skin that
revealed that high-stress-concentration areas are susceptible to skin
cracking. AD 2013-12-07 requires for tailboom assemblies with 8,600 or
more hours time-in-service (TIS), or with an unknown number of hours
TIS, before the first flight of each day, inspecting the tailboom
assembly for a crack; or within 25 hours TIS, or 30 days, whichever
comes first, and thereafter at intervals not to exceed 50 hours TIS,
inspecting for a crack around each fastener and above the edge of the
upper stabilizer support. AD 2013-12-07 also requires for certain
tailboom assemblies with 6,900 or more hours TIS, within 25 hours TIS
or 30 days, whichever occurs first, inspecting the tailboom assembly
for a crack by using either a 10X or higher power magnifying glass and
thereafter inspecting at intervals not to exceed 150 hours TIS; or by
eddy current inspecting and thereafter inspecting at intervals not to
exceed 500 hours TIS.
Additionally, AD 2013-12-07 requires, within 100 hours TIS or at
the next tailboom inspection, whichever occurs first, and thereafter at
intervals not to exceed 300 hours TIS, inspecting the tailboom assembly
for a crack, loose rivet, or other damage. Depending on the inspection
results, AD 2013-12-07 requires if there is a crack, before further
flight replacing the tailboom assembly with an airworthy part.
The FAA issued AD 2014-04-07, Amendment 39-17766 (79 FR 35481, June
23, 2014) (AD 2014-04-07) for Bell Helicopter Textron Canada (now Bell
Textron Canada Limited) Model 407 helicopters serial numbers (S/Ns)
53000 through 53475, with tailboom P/N 407-030-801-101, -105, or -107,
or 407-530-014-101 or -103, installed. AD 2014-04-07 was prompted by
additional reports of cracked tailboom skins. AD 2014-04-07 requires
for certain part-numbered tailbooms that have not been modified,
conducting daily preflight checks of the tailboom for a crack; and for
tailbooms with 600 or more hours TIS, within 25 hours TIS, and
thereafter at intervals not to exceed 50 hours TIS, visually inspecting
the tailboom for a crack using a 10X or higher power magnifying glass,
and within 600 hours TIS but not later than 30 days modifying and re-
identifying certain part-numbered tailbooms, and installing an improved
horizontal stabilizer assembly. AD 2014-04-07 also requires for certain
part-numbered tailbooms, after the modification, before further flight,
establishing a component history card or equivalent record, and
revising the existing ALS of the maintenance manual to reflect a new
life limit.
AD 2014-04-07 also requires, for certain part-number tailbooms,
within 25 hours TIS or 30 days, whichever occurs first, daily visual
inspections of the tailboom for a crack, and within 100 hours TIS and
thereafter at intervals not to exceed 100 hours TIS, using a 10X or
higher power magnifying glass, inspecting each tailboom for a loose
rivet, crack, skin corrosion, or any other damage. Depending on the
inspection results, AD 2014-04-07 requires corrective actions,
including, if there is a crack, replacing the tailboom assembly before
further flight.
Actions Since AD 99-23-18, AD 2005-03-07, AD 2013-12-07, and AD 2014-
04-07 Were Issued
Since the FAA issued AD 99-23-18, AD 2005-03-07, AD 2013-12-07, and
AD 2014-04-07, Transport Canada, which is the aviation authority for
Canada, issued AD CF-2021-34, dated October 22, 2021 (Transport Canada
AD CF-2021-34), to correct an unsafe condition for Bell Textron Canada
Limited Model 407 helicopters, S/N 53000 through 53900, 53911 through
54166, and 54300 and subsequent. Transport Canada advises of a report
of a crack on the tailboom lower skin due to fatigue damage, which
could affect the structural integrity of the tailboom. Transport Canada
advises that Bell Textron Canada Limited issued a revision to the ALS,
which adds a new inspection zone for tailboom assemblies to address the
unsafe condition.
Accordingly, Transport Canada AD CF-2021-34 requires compliance
with Bell BHT-407-MPI, Chapter 04, ALS, Issue 3, dated June 21, 2021,
of Bell Model 407 Maintenance Planning Information, PMC-407-97499-
01000-00, Issue No. 005, dated July 6, 2022 (BHT-407-MPI, ALS Issue 3),
which includes maintenance tasks and life limits for the tailboom and
other parts. The FAA is proposing this AD to prevent failure of a part,
which could result in loss of control of the helicopter.
Additionally, although AD 99-23-18 and AD 2005-03-07 were prompted
by unsafe conditions not related to the tailboom crack that prompted
this proposed AD, the actions required to address the unsafe conditions
in AD 99-23-18 and AD 2005-03-07 are included in BHT-407-MPI, ALS Issue
3. Therefore, the FAA is superseding AD 99-23-18, AD 2005-03-07, AD
2013-12-07, and AD 2014-04-07, in order to reduce the burden on
operators by requiring compliance with a single AD in lieu of multiple
FAA ADs.
AD 99-23-18 requires reducing the life limit for drive ring set P/N
406-010-126-107 from 49,000 RIN to 48,000 RIN, and replacing each part
that has exceeded its life limit. BHT-407-MPI, ALS Issue 3 states the
life limit for drive
[[Page 50007]]
ring set P/N 406-010-126-107 is 100,000 RIN.
AD 2005-03-07 requires establishing a maximum accumulated RIN for
certain crosstube assemblies of 5,000 RIN and replacing any crosstube
assembly before it exceeds the maximum accumulated RIN. BHT-407-MPI,
ALS Issue 3 adds an additional life limit to certain part-numbered
crosstube assemblies of 2,500 landings or 5,000 RIN.
AD 2013-12-07 requires for tailboom assemblies with P/N 407-030-
801-201, 407-030-801-203, or 407-030-801-205 and with 8,600 or more
hours TIS, or with an unknown number of hours TIS, inspecting the
tailboom assembly for a crack within 25 hours TIS or 30 days, whichever
comes first; and thereafter at intervals not to exceed 50 hours TIS,
inspecting for a crack. AD 2013-12-07 also requires for tailboom
assemblies with 6,900 or more hours TIS, inspecting the tailboom
assembly for a crack within 25 hours TIS or 30 days, whichever comes
first. Thereafter AD 2013-12-07 requires either inspecting using a 10X
or higher power magnifying glass and thereafter repeating that
inspection at intervals not to exceed 150 hours TIS or eddy current
inspecting and thereafter repeating the eddy current inspection at
intervals not to exceed 500 hours TIS. AD 2013-12-07 also requires
within 100 hours TIS or at the next tailboom inspection, whichever
comes first, and thereafter at intervals not to exceed 300 hours TIS,
inspecting the tailboom assembly for a loose rivet, crack, or other
damage.
BHT-407-MPI, ALS Issue 3 adds tailboom assembly P/N 407-530-013-105
and successive dash numbers, and also specifies for tailboom assembly
P/N 407-530-013-105 and successive dash numbers and P/N 407-030-801-201
and successive dash numbers, inspecting for a crack every 300 hours;
and for tailbooms that have accumulated 6,900 or more hours in service
inspecting every 150 hours using a 10X magnifying glass inspection
method, or eddy current inspecting every 500 hours; and for tailboom
assemblies that have accumulated 8,600 or more hours in service, or
with total time unknown, inspecting for a crack either with a daily
visual inspection or with a 10X magnifying glass inspection method at
intervals not to exceed 50 hours. Additionally, BHT-407-MPI, ALS Issue
3 specifies additional inspection zones, intervals, and criteria.
AD 2014-04-07 requires modifying and re-identifying tailboom P/N
407-030-801-101 as 407-530-014-101, and P/N 407-030-801-105 as P/N 407-
530-014-103. AD 2014-04-07 also requires for tailboom P/N 407-530-014-
101 and -103, and P/N 407-030-801-107, establishing a retirement life
of 5,000 hours TIS, and daily checks for a crack and recurring
inspections using a 10X or higher power magnifying glass at intervals
not to exceed 100 hours TIS for a loose rivet, a crack, skin corrosion,
or other damage. BHT-407-MPI, ALS Issue 3 specifies for tailboom P/N
407-530-014-101 and successive dash numbers, and P/N 407-030-801-107
and successive dash numbers, daily and recurring inspections for a
crack every 100 hours TIS. BHT-407-MPI, ALS Issue 3 also revises the
inspection areas.
FAA's Determination
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 is proposing this AD after evaluating all
known relevant information and determining that the unsafe condition
described previously is likely to exist or develop on other helicopters
of the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed BHT-407-MPI, ALS Issue 3, which specifies certain
actions and associated thresholds and intervals, including life limits
and maintenance tasks. These requirements (airworthiness limitations)
include new inspection zones and new maintenance tasks (e.g.,
inspections for cracks) with new compliance times.
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.
Proposed AD Requirements in This NPRM
This proposed AD would supersede AD 99-23-18, AD 2005-03-07, AD
2013-12-07, and AD 2014-04-07, and would require incorporating into
existing maintenance records requirements (airworthiness limitations),
which are identified in BHT-407-MPI, ALS Issue 3, as described
previously.
ADs Mandating Airworthiness Limitations
The FAA has previously mandated airworthiness limitations by
mandating each airworthiness limitation task (e.g., inspections and
replacements (life limits)) as an AD requirement or issuing ADs that
require revising the ALS of the existing maintenance manual or
instructions for continued airworthiness to incorporate new or revised
inspections and life limits. This proposed AD, however, would require
operators to incorporate into maintenance records required by 14 CFR
91.417(a)(2) or 135.439(a)(2), as applicable for your rotorcraft, the
requirements (airworthiness limitations) identified in the ALS service
information, as described previously. The FAA does not intend this as a
substantive change. For these ADs, the ALS requirements for operators
are the same but are complied with differently. Requiring the
incorporation of the new ALS requirements into the existing maintenance
records, rather than requiring individual ALS tasks (e.g., repetitive
inspections and replacements), requires operators to record AD
compliance once after updating the maintenance records, rather than
after every time the ALS task is completed.
Differences Between This Proposed AD and Transport Canada AD CF-2021-34
or the Service Information
Transport Canada AD CF-2021-34 does not supersede any previously
issued Transport Canada ADs, whereas this proposed AD would supersede
FAA AD 99-23-18, AD 2005-03-07, AD 2013-12-07, and AD 2014-04-07. The
airworthiness limitations specified in Transport Canada AD CF-2021-34
encompass the requirements of AD 99-23-18, AD 2005-03-07, AD 2013-12-
07, and AD 2014-04-07.
Additionally, Transport Canada AD CF-2021-34 is applicable to
certain serial-numbered Bell Textron Canada Limited Model 407
helicopters, whereas this proposed AD would be applicable to all
serial-numbered Model 407 helicopters.
The service information specifies replacing each component before
exceeding the applicable airworthiness life limit, accomplishing all
applicable maintenance tasks within the defined thresholds and
intervals, and performing the specified corrective action(s) if a
defect is found during the inspection, whereas this proposed AD would
require incorporating requirements (airworthiness limitations) into
existing maintenance records within 30 days after the effective date of
the AD.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 791 helicopters of U.S. Registry. Labor rates are estimated at
$85 per work-hour. Based on these numbers, the FAA
[[Page 50008]]
estimates the following costs to comply with this proposed AD.
Incorporating requirements (airworthiness limitations) into
existing maintenance records would take about 2 work-hours for an
estimated cost of $170 per helicopter and $134,470 for the U.S. fleet.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
0
a. Removing Airworthiness Directive 99-23-18, Amendment 39-11414 (64 FR
61784, November 15, 1999); Airworthiness Directive 2005-03-07,
Amendment 39-13963 (70 FR 7016, February 10, 2005); Airworthiness
Directive 2013-12-07, Amendment 39-17485 (78 FR 38546, June 27, 2013);
and Airworthiness Directive 2014-04-07, Amendment 39-17766 (79 FR
35481, June 23, 2014); and
0
b. Adding the following new airworthiness directive:
Bell Textron Canada Limited (Type Certificate Previously Held by
Bell Helicopter Textron Canada Limited): Docket No. FAA-2022-0992;
Project Identifier MCAI-2022-00173-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by September 29, 2022.
(b) Affected ADs
This AD replaces the ADs specified in paragraphs (b)(1) through
(4) of this AD.
(1) AD 99-23-18, Amendment 39-11414 (64 FR 61784, November 15,
1999).
(2) AD 2005-03-07, Amendment 39-13963 (70 FR 7016, February 10,
2005).
(3) AD 2013-12-07, Amendment 39-17485 (78 FR 38546, June 27,
2013).
(4) AD 2014-04-07, Amendment 39-17766 (79 FR 35481, June 23,
2014).
Note 1 to paragraph (b): The requirements of this AD capture the
latest tasks and life limits required to prevent the unsafe
conditions addressed by the ADs that are identified in paragraphs
(b)(1) through (4) of this AD.
(c) Applicability
This AD applies to all Bell Textron Canada Limited (type
certificate previously held by Bell Helicopter Textron Canada
Limited) Model 407 helicopters, certificated in any category.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 5300, Fuselage
Structure.
(e) Unsafe Condition
This AD was prompted by a report of a crack on the tailboom
lower skin due to fatigue damage and the issuance of new and more
restrictive airworthiness limitations. The FAA is issuing this AD to
prevent failure of a part, which could result in loss of control of
the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within 30 days after the effective date of this AD, incorporate
into maintenance records required by 14 CFR 91.417(a)(2) or
135.439(a)(2), as applicable for your helicopter, the requirements
(airworthiness limitations) specified in Bell BHT-407-MPI, Chapter
04, Airworthiness Limitations Schedule, Issue 3, dated June 21,
2021, of Bell Model 407 Maintenance Planning Information, PMC-407-
97499-01000-00, Issue No. 005, dated July 6, 2022.
(h) Provisions for Alternative Requirements (Airworthiness Limitations)
After the actions required by paragraph (g) of this AD have been
done, no alternative requirements (airworthiness limitations) are
allowed unless they are approved as an alternative method of
compliance (AMOC) in accordance with the procedures specified in
paragraph (j)(1) of this AD.
(i) Special Flight Permits
Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199, provided no passengers are onboard.
(j) 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 (k)(1) of
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#c0f9ed819693ed818992edf7f3f0ed818d8f8380a6a1a1eea7afb6"><span class="__cf_email__" data-cfemail="f2cbdfb3a4a1dfb3bba0dfc5c1c2dfb3bfbdb1b2949393dc959d84">[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.
(k) Related Information
(1) For more information about this AD, contact Andrea Jimenez,
Aerospace Engineer, COS Program Management Section, Operational
Safety Branch, Compliance & Airworthiness Division, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email <a href="/cdn-cgi/l/email-protection#1c7d72786e797d32767571797279665c7a7d7d327b736a"><span class="__cf_email__" data-cfemail="55343b312730347b3f3c38303b302f153334347b323a23">[email protected]</span></a>.
(2) For service information identified in this AD, contact Bell
Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J
1R4, Canada; telephone 1-450-437-2862 or 1-800-363-8023; fax 1-450-
433-0272; email <a href="/cdn-cgi/l/email-protection#28585a474c5d4b5c5b5d5858475a5c684a4d44444e44414f405c064b4745"><span class="__cf_email__" data-cfemail="48383a272c3d2b3c3b3d3838273a3c082a2d24242e24212f203c662b2725">[email protected]</span></a>; or at
<a href="http://www.bellflight.com/support/contact-support">www.bellflight.com/support/contact-support</a>. You may view this
referenced 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.
[[Page 50009]]
(3) The subject of this AD is addressed in Transport Canada AD
CF-2021-34, dated October 22, 2021. You may view the Transport
Canada AD on the internet at <a href="http://www.regualtions.gov">www.regualtions.gov</a> in Docket No. FAA-
2022-0992.
Issued on August 4, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-17140 Filed 8-12-22; 8:45 am]
BILLING CODE 4910-13-P
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</html>Indexed from Federal Register on August 15, 2022.
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.