Proposed Rule2022-12100
Airworthiness Directives; Bell Textron Inc. (Type Certificate Previously Held by Bell Helicopter Textron Inc.) Helicopters
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Published
June 7, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for all Bell Textron Inc. (type certificate previously held by Bell Helicopter Textron Inc.), Model 204B, 205A, 205A-1, 205B, and 210 helicopters. This proposed AD was prompted by events involving failure of the tail boom attachment structure. This proposed AD would require revising the existing Rotorcraft Flight Manual (RFM) for your helicopter and repetitive inspections of structural components that attach the tail boom to the fuselage. Depending on the results of the inspections, this proposed AD would require removing certain parts from service or re-bonding the structure. The FAA is proposing this AD to address the unsafe condition on these products.
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<title>Federal Register, Volume 87 Issue 109 (Tuesday, June 7, 2022)</title>
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[Federal Register Volume 87, Number 109 (Tuesday, June 7, 2022)]
[Proposed Rules]
[Pages 34587-34591]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-12100]
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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. 109 / Tuesday, June 7, 2022 /
Proposed Rules
[[Page 34587]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0600; Project Identifier AD-2021-01160-R]
RIN 2120-AA64
Airworthiness Directives; Bell Textron Inc. (Type Certificate
Previously Held by Bell Helicopter Textron Inc.) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Bell Textron Inc. (type certificate previously held by Bell
Helicopter Textron Inc.), Model 204B, 205A, 205A-1, 205B, and 210
helicopters. This proposed AD was prompted by events involving failure
of the tail boom attachment structure. This proposed AD would require
revising the existing Rotorcraft Flight Manual (RFM) for your
helicopter and repetitive inspections of structural components that
attach the tail boom to the fuselage. Depending on the results of the
inspections, this proposed AD would require removing certain parts from
service or re-bonding the structure. 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 July 22,
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="https://www.regulations.gov">https://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 above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Bell
Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (450) 437-
2862 or (800) 363-8023; fax (450) 433-0272; email
<a href="/cdn-cgi/l/email-protection#58282a373c2d3b2c2b2d2828372a2c183a3d34343e34313f302c763b3735"><span class="__cf_email__" data-cfemail="e9999b868d9c8a9d9a9c9999869b9da98b8c85858f85808e819dc78a8684">[email protected]</span></a>; or at <a href="https://www.bellflight.com/support/contact-support">https://www.bellflight.com/support/contact-support</a>.
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-2022-0600; 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, any comments
received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Ameet Shrotriya, Aviation Safety
Engineer, DSCO Branch, Compliance & Airworthiness Division, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177-1524; phone: (817) 222-5525;
email: <a href="/cdn-cgi/l/email-protection#a2e3cfc7c7d68cf1cad0cdd6d0cbdbc3e2c4c3c38cc5cdd4"><span class="__cf_email__" data-cfemail="de9fb3bbbbaaf08db6acb1aaacb7a7bf9eb8bfbff0b9b1a8">[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-2022-0600; Project Identifier
AD-2021-01160-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="https://www.regulations.gov">https://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 Ameet
Shrotriya, Aviation Safety Engineer, DSCO Branch, Compliance &
Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177-1524; phone: (817) 222-5525; email: <a href="/cdn-cgi/l/email-protection#52133f3737267c013a203d26203b2b33123433337c353d24"><span class="__cf_email__" data-cfemail="eaab878f8f9ec4b98298859e9883938baa8c8b8bc48d859c">[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.
Background
The FAA issued AD 2021-15-14, Amendment 39-21661 (86 FR 39942, July
26, 2021) (AD 2021-15-14), for various restricted category helicopters.
AD 2021-15-14 was prompted by an accident involving a Model UH-1B
helicopter and two forced landings involving Model UH-1H and UH-1F
helicopters, due to tail boom attachment structure failures. Each of
the three events involved a failure of the upper left-hand (LH) tail
boom attachment fitting, which is the most heavily loaded of the four
tail boom attach points. AD 2021-15-14 requires revising the existing
RFM for your helicopter to incorporate pre- flight checks; removing
paint and sealant, and cleaning; repetitive inspections of structural
components that attach the tail boom to the fuselage; and depending on
the outcome of the inspections, repairing or replacing components, or
re-bonding the structure. The FAA issued AD 2021-15-14 to address
fatigue cracking of tail boom attachment fittings, cap angles,
longerons, and bolts. Due to their similarity to the Model UH-1B, UH-
1H, and UH-1F helicopters, the FAA has
[[Page 34588]]
determined that Bell Textron Inc., Model 204B, 205A, 205A-1, 205B, and
210 helicopters are affected by the same unsafe condition. Therefore,
the FAA proposes to adopt a new AD for Bell Textron Inc., Model 204B,
205A, 205A-1, 205B, and 210 helicopters. This proposed AD would require
revising the existing RFM for your helicopter to incorporate pre-flight
checks; removing paint and sealant, and cleaning; repetitive
inspections of structural components that attach the tail boom to the
fuselage; and depending on the outcome of the inspections, repairing or
replacing components, or re-bonding the structure.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Related Service Information
The FAA reviewed Bell Helicopter Maintenance & Overhaul
Instructions BHT-204B-M&O, Revision 13, dated November 10, 2021 and
Bell Helicopter Maintenance Manual BHT-205A1-MM-1, Revision 11, dated
June 8, 2020. This service information specifies procedures for
inspecting the tail boom assembly.
Proposed AD Requirements in This NPRM
This proposed AD would require revising the existing RFM for your
helicopter to add before each flight and before the first flight of the
day pre-flight checks of the tail boom attachment. Incorporating the
RFM revision may be performed by the owner/operator (pilot) holding at
least a private pilot certificate and must be entered into the aircraft
records showing compliance with the proposed AD in accordance with 14
CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must
be maintained as required by 14 CFR 91.417 or 135.439. This is an
exception to the FAA's standard maintenance regulations.
This proposed AD would also require removing excess paint and
sealant from, and cleaning, certain tail boom attachment structures;
repetitive inspections for scratches, nicks, gouges, tears, corrosion,
cracks, bond separation, loose, missing, and smoking rivets, buckling,
distortion, number of attachment bolt exposed threads, and attachment
bolt movement. This proposed AD would then require repairing any
scratches, nicks, gouges, tears, and corrosion within allowable limits
or would require removing from service components with scratches,
nicks, gouges, tears, and corrosion that exceed allowable limits,
removing from service components with any cracks, buckling, or
distortion, and removing from service and replacing loose, missing, or
smoking rivets.
Finally, this proposed AD would require re-bonding any structure
with dis-bonds, and removing loose bolts and self-locking nuts from
service, and replacing them with new bolts and new self-locking nuts.
After the first flight following any bolt replacement, retorquing any
replaced bolt would be required.
Costs of Compliance
The FAA estimates that this proposed AD would affect 57 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 proposed AD.
Revising the RFM for your helicopter would take about 0.5 work-
hour, for an estimated cost of $43 per helicopter and $2,451 for the
U.S. fleet.
Removing excess paint and sealant, and cleaning all eight tail boom
attachment fittings would take about 5 work-hours and a nominal
materials cost, for an estimated cost of $425 per helicopter per
instance and $24,225 for the U.S. fleet per instance.
Inspecting the tail boom structural components and attached
hardware would take about 16 work-hours for an estimated cost of $1,360
per helicopter and $77,520 for the U.S. fleet per inspection cycle.
Replacing a tail boom attachment fitting would take about 33 work-
hours and parts would cost about $1,500 for an estimated cost of $4,305
per helicopter.
Replacing a tail boom longeron bond assembly would take about 42
work-hours and parts would cost up to about $21,270 for an estimated
cost of up to $24,840 per helicopter.
Replacing a fuselage attachment fitting would take about 45 work-
hours and parts would cost about $1,838 for an estimated cost of $5,663
per helicopter.
Replacing a fuselage cap angle would take about 42 work-hours and
parts would cost about $1,827 for an estimated cost of $5,397 per
helicopter.
Replacing an attachment bolt and self-locking nut would take about
1 work-hour and parts would cost about $313 for an estimated cost of
$398 per helicopter.
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 above, 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]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
Bell Textron Inc. (Type Certificate Previously Held by Bell
Helicopter Textron Inc.): Docket No. FAA-2022-
[[Page 34589]]
0600; Project Identifier AD-2021-01160-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by July 22, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bell Textron Inc. (type certificate
previously held by Bell Helicopter Textron Inc.) Model 204B, 205A,
205A-1, 205B, and 210 helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) 5302, Rotorcraft Tail
Boom.
(e) Unsafe Condition
This AD was prompted by an accident and incidents involving
failure of the tail boom attachment structure. The FAA is issuing
this AD to address fatigue cracking of tail boom attachment
fittings, cap angles, longerons, and bolts. The unsafe condition, if
not addressed, could result in separation of the tail boom from the
helicopter and subsequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Before further flight, revise the limitations section of the
existing Rotorcraft Flight Manual (RFM) for your helicopter by
adding the information in Figure 1 to paragraph (g)(1) of this AD or
by inserting a copy of this AD. The action required by this
paragraph may be done by the owner/operator (pilot) holding at least
a private pilot certificate and must be entered into the aircraft
records showing compliance with this AD by following 14 CFR 43.9
(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417or 135.439.
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[GRAPHIC] [TIFF OMITTED] TP07JN22.000
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(2) Within 25 hours time-in-service (TIS):
(i) Open the oil cooler/baggage compartment door on the right
hand side of the helicopter to gain access to the interior of the
tail boom.
(ii) Remove paint and stray sealant and clean the eight attach
fittings (four on the tail boom side and four on the fuselage side).
Remove paint and stray sealant and clean the four cap angles,
forward of the fuselage fittings, for at least 12 inches from the
end of the fittings. Remove paint and stray sealant and clean the
four longerons, aft of the tail
[[Page 34591]]
boom fittings, for at least 12 inches from the end of the fittings.
It is only necessary to remove the topcoat. Primer may be left in
place and edge and fillet sealant may be left in place. If any
primer or edge or fillet sealant is removed, before further flight,
reapply the removed primer and sealant.
Note 1 to paragraph (g)(2)(ii): On some models, the baggage
compartment floor and net must be removed to gain access to the
lower fuselage attach fittings and cap angles.
(iii) With an additional person pushing on the tail boom at the
third vertical rivet line aft of the trailing edge of the elevator
with both hands and gradually applying and relieving pressure using
body weight a minimum of three times in each of the following
directions: Inboard pushing from the left; inboard pushing from the
right; and upward pushing from the bottom; and using a bright light
and borescope, inspect each of the four tail boom attach structures
for cracks, bond separation, and loose rivets. On the fuselage side,
inspect the fittings and the cap angles running forward from the
fittings, paying particular attention to the fitting sections near
the rivets closest to the attach bolts and the cap angle rivets next
to the fittings. On the tail boom side, inspect the fittings and the
longerons running aft from the fittings, paying particular attention
to the fitting sections near the rivets closest to the attach bolts.
Without pushing on the tail boom, and using a bright light and
borescope, inspect each of the four tail boom attach structures for
scratches, nicks, gouges, tears, corrosion, buckling, and
distortion, and for loose, missing, and smoking rivets. If there are
any scratches, nicks, gouges, tears, or corrosion within allowable
limits, before further flight, repair the affected components. If
there are any scratches, nicks, gouges, tears, or corrosion that
exceed allowable limits, or any cracks, buckling, or distortion, or
loose, missing, or smoking rivets, before further flight, remove the
affected components from service. If there is any bond separation,
before further flight, re-bond the affected components.
Note 2 to paragraph (g)(2)(iii): It is not required to push on
the tail boom if it cannot be reached from ground level while
inspecting for cracks, bond separation, and loose rivets.
(iv) Inspect the tail boom attach bolts for exposed threads. If
there is less than one full thread or more than three threads
exposed, before further flight, remove the bolt and self-locking nut
from service and replace with a new bolt and new self-locking nut.
(v) Inspect each of the four tail boom attach bolts for movement
by either applying the required installation torque in the
tightening direction only, or by inspecting for torque stripe
misalignment if present and attempting to rotate the bolt by hand.
If a bolt is under-torqued, a torque stripe is misaligned, or a bolt
moves, before further flight, remove the bolt and self-locking nut
from service and replace with a new bolt and new self-locking nut.
(vi) After the first flight following any bolt replacement as
required by paragraph (g)(2)(iv) or (v) of this AD, retorque any
replaced bolt by applying torque in accordance with the existing
maintenance instructions for your helicopter in the tightening
direction only and then apply a torque stripe on the bolt head.
(3) Within 25 hours TIS after the effective date of this AD, and
thereafter at intervals not to exceed 25 hours TIS, perform the
actions required by paragraphs (g)(2)(ii) through (vi) of this AD at
the upper left-hand tail boom attach points.
(4) Within 25 hours TIS after the effective date of this AD, and
thereafter at intervals not to exceed 100 hours TIS, perform the
actions required by paragraphs (g)(2)(ii) through (vi) of this AD at
all four tail boom attach points.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, DSCO Branch, Compliance & Airworthiness
Division, FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the certification office,
send it to the attention of the person identified in paragraph (i)
of this AD. You may email your request to: <a href="/cdn-cgi/l/email-protection#ac9581edfffb819d959c81efe3ffeccacdcd82cbc3da"><span class="__cf_email__" data-cfemail="bd8490fceeea908c848d90fef2eefddbdcdc93dad2cb">[email protected]</span></a>@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(i) Related Information
For more information about this AD, contact Ameet Shrotriya,
Aviation Safety Engineer, DSCO Branch, Compliance & Airworthiness
Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177-1524;
phone: (817) 222-5525; email: <a href="/cdn-cgi/l/email-protection#c584a8a0a0b1eb96adb7aab1b7acbca485a3a4a4eba2aab3"><span class="__cf_email__" data-cfemail="acedc1c9c9d882ffc4dec3d8dec5d5cdeccacdcd82cbc3da">[email protected]</span></a>.
Issued on May 31, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022-12100 Filed 6-6-22; 8:45 am]
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