[Federal Register Volume 87, Number 51 (Wednesday, March 16, 2022)]
[Rules and Regulations]
[Pages 14772-14778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-05487]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1120; Project Identifier 2019-SW-056-AD; Amendment 
39-21962; AD 2022-05-10]
RIN 2120-AA64


Airworthiness Directives; Goodrich Externally-Mounted Hoist 
Assemblies

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
various model helicopters with certain part-numbered Goodrich 
externally-mounted hoist assemblies (hoists) installed. This AD was 
prompted by hoists failing lower load limit inspections. This AD 
requires replacing unmodified hoists, installing placards, revising the 
existing Rotorcraft Flight Manual (RFM) for your helicopter, 
deactivating or removing a hoist if a partial peel out occurs, 
reviewing the helicopter's hoist slip load test records, repetitively 
inspecting the hoist cable and overload clutch (clutch), and reporting 
information to the manufacturer. This AD also requires establishing 
operating limitations on the hoist and prohibits installing an 
unmodified hoist. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective April 20, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of April 20, 2022.

ADDRESSES: For Goodrich service information identified in this final 
rule, contact Collins Aerospace; 2727 E Imperial Hwy., Brea, CA 92821; 
telephone (714) 984-1461; email [email protected]; or at https://www.collinsaerospace.com/. You may view the referenced service 
information at the FAA, Office of the Regional Counsel, Southwest 
Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. For 
information on the availability of this material at the FAA, call (817) 
222-5110. It is also available at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-1120.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2020-1120; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The AD docket contains this final rule, the 
European Union Aviation Safety Agency (EASA) AD, any comments received, 
and other information. The street address for Docket Operations is U.S. 
Department of Transportation, Docket Operations, M-30, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 
20590.

FOR FURTHER INFORMATION CONTACT: Kristi Bradley, Program Manager, COS 
Program Management Section, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone (817) 222-5110; 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 various model 
helicopters with certain part-numbered externally-mounted Goodrich 
hoists installed. The NPRM published in the Federal Register on 
December 11, 2020 (85 FR 79930). In the NPRM, the FAA proposed to 
require replacing unmodified hoists, installing placards, revising the 
existing RFM for your helicopter, deactivating or removing a hoist if a 
partial peel out occurs, reviewing the helicopter's hoist slip load 
test records, repetitively inspecting the hoist cable and clutch, and 
reporting information to the manufacturer. The NPRM was prompted by a 
series of EASA ADs, the most recent at that time being EASA AD 2015-
0226R5, Revision 5, dated July 23, 2020 (EASA AD 2015-0226R5), to 
correct an unsafe condition for various model helicopters with a 
Goodrich externally-mounted hoist with one of the following part 
numbers (P/Ns) or base P/Ns installed: 42315, 42325, 44301-10-1, 44301-
10-2, 44301-10-4, 44301-10-5, 44301-10-6, 44301-10-7, 44301-10-8, 
44301-10-9, 44301-10-10, 44301-10-11, 44311, 44312, 44314, 44315, 
44316, or 44318. EASA advised of an initial incident of a rescue hoist 
containing a dummy test load of 552 lbs. that reeled-out without 
command of the operator and impacted the ground during a maintenance 
check flight because the overload clutch had failed. EASA stated that 
this condition, if not detected and corrected, could lead to further 
cases of in-flight loss of the hoist load, possibly resulting in injury 
to persons on the ground or in a hoisting accident.
    Accordingly, EASA AD 2015-0226R5 required a records review to 
determine if the cable had exceeded the allowable limit in previous 
load testing, a repetitive load check and test of the clutch slip 
value, removal or deactivation of a hoist that could not be tested due 
to lack of approved instructions, replacement of the old clutch P/N 
with a new clutch developed by Goodrich to mitigate some of the factors 
resulting in clutch degradation, periodic replacement of the hoist, 
reduction of the maximum allowable load on the hoist, addition of 
operational limitations to the RFM, and replacement of the hoist after 
a partial peel out. EASA AD 2015-0226R5 also prohibited the 
installation of a replacement cable that has exceeded the allowable 
limit in previous load testing. EASA considered AD 2015-0226R5 to be 
interim action and advised further AD action may follow.
    The FAA issued a supplemental notice of proposed rulemaking (SNPRM) 
to amend 14 CFR part 39 by adding an AD that would apply to various 
model helicopters with certain part-numbered externally-mounted 
Goodrich hoists installed. The SNPRM published in the Federal Register 
on September 30, 2021 (86 FR 54129). The SNPRM proposed to revise the 
NPRM by adding a figure and revising certain requirements, including 
changes to the temperatures in the

[[Page 14773]]

maximum hoist load limitations and adding the cost of a (field) load 
check tool. The SNPRM was prompted by changes from the public comments, 
which expanded the scope of the NPRM.
    Although the NPRM and SNPRM discussed the unsafe condition as 
described by EASA in EASA AD 2015-0226R5, the FAA based most of the 
proposed requirements in both the NPRM and the SNPRM on service 
information issued by Goodrich for all helicopter models with an 
affected hoist. For the replacement intervals proposed in paragraph 
(g)(1) of the NPRM and SNPRM, the FAA based those actions on portions 
of the EASA AD that are not model specific.

Actions Since the SNPRM Was Issued

    Since the FAA issued the SNPRM, EASA has revised EASA AD 2015-
0226R5 and issued EASA AD 2015-0226R6, Revision 6, dated December 8, 
2021, and corrected December 20, 2021 (EASA AD 2015-0226R6). EASA AD 
2015-0226R6 adds a new helicopter model-specific replacement/overhaul 
interval for affected hoists with a new overload clutch. After 
reviewing the changes in EASA AD 2015-0226R6, the FAA has determined 
that no changes to this AD are necessary.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from Bell Textron Canada Limited (Bell 
Canada), Collins Aerospace, and Transport Canada. The following 
presents the comments received on the SNPRM and the FAA's response to 
each comment.

Request Regarding the Costs of Compliance

    Collins Aerospace commented that two new potential costs could 
impact operators: Groundings from an inability to update the fleet and 
contract penalties for operational contracts requiring the use of a 
600-lb rated hoist.
    The cost analysis in AD rulemaking actions includes only the costs 
associated with complying with the AD, which does not include indirect 
costs such as down-time and loss of revenue.

Request To Change the AD for Bell Canada Model 429 and 430 Helicopters

    Bell Canada and Transport Canada stated that, because Canada is the 
state of design for Model 429 and 430 helicopters, the FAA should 
review Transport Canada AD CF-2017-23, dated July 7, 2017 (Transport 
Canada AD CF-2017-23), and revise the FAA's proposed AD accordingly. 
The commenters stated that they discussed the corrective actions in 
Transport Canada AD CF-2017-23 and tailored its limitations and 
operating parameters specifically for Bell Canada Model 429 and 430 
helicopters. Bell Canada stated that because the related EASA AD was 
issued unilaterally, the mitigations in Transport Canada AD CF-2017-23 
are better suited for Model 429 and 430 helicopters than those in the 
EASA AD.
    The FAA reviewed Transport Canada AD CF-2017-23, which is 
applicable to, and has some different requirements for, certain Bell 
Canada Model 429 and 430 helicopters. This FAA AD applies to affected 
Goodrich hoists, regardless of the model helicopter they are installed 
on, to address the risk to the fleet independent of the helicopter 
installation. Accordingly, the FAA based its AD on Goodrich's service 
information and not on any model-specific requirements. Operators may 
request approval of model-specific corrective actions as an alternative 
method of compliance (AMOC) under the provisions of paragraph (h) of 
this AD.

Request Regarding Compliance Time for Hoist Replacement

    Collins Aerospace requested the FAA extend the compliance time for 
replacing an affected hoist with a hoist that has an improved overload 
clutch assembly from 12 months to 24 months. In support, Collins 
Aerospace stated 24 months is an acceptable time based on improved data 
from the initial load checks and subsequent checks with a load check 
tool. Additionally, Collins Aerospace stated it does not have the 
capacity to provide improved overload clutch assemblies for the entire 
fleet within 12 months.
    The FAA agrees because no additional reports of low pulling hoists 
have been received since issuance of the SNPRM. The FAA has revised 
this final rule accordingly.

Request To Prohibit Maneuvering

    In the SNPRM, the FAA proposed to require a placard and RFM 
limitation that warned the pilot about excessive maneuvering with a 
load on an extended cable and limited the maximum sustained bank angle 
to 20 degrees. Bell Canada stated that limits on bank angle (and 
pendulum angle) are difficult to monitor by aircrew and will increase 
crew workload, and therefore prohibiting maneuvering with load on 
extended cable is necessary to manage the risk of clutch slippage. The 
FAA infers that Bell Canada is requesting the FAA prohibit maneuvering 
with load on an extended cable for Model 429 and 430 helicopters.
    The FAA disagrees with changing the flight limitation from a bank 
angle limit to a maneuvering prohibition. The FAA determined that 
limiting the bank angle in conjunction with a reduced maximum load 
mitigates the unsafe condition. The attitude indicator, which is used 
by the pilot to monitor the bank angle while maneuvering an external 
load, is in the pilot's normal field of view and is regularly 
monitored; therefore, any additional workload is minimal. The FAA does 
agree that requiring the aircrew to monitor the lateral pendulum angle 
of the hoist cable with respect to the helicopter's vertical axis would 
not be an acceptable limitation because it would not be measurable or 
enforceable.

Requests Regarding the Maximum Hoist Load Limitations

    In the SNPRM, the FAA proposed to require a placard and revision to 
the RFM to reduce the weight limitations for the hoist load based on 
the outside air temperature. Bell Canada stated that the FAA's proposed 
limitations include a de-rating factor of 50 lbs, which is not 
warranted for Bell Canada Model 429 and 430 helicopters. In support, 
Bell Canada stated that the de-rating factor was established to 
accommodate certain maneuvering, which has been prohibited for the Bell 
Canada products.
    The FAA determined the de-rating factor is necessary because it 
directly correlates to the bank angle limitation required by this AD.
    Collins Aerospace requested the FAA change the proposed maximum 
hoist load limitations to distinguishing between non-modified hoists 
(without the number ``4'' as the first digit of its serial number (S/
N)) and modified hoists with a new clutch (with the number ``4'' as the 
first digit of its S/N). Collins Aerospace stated that after EASA AD 
2015-0226R1 was issued, Goodrich performed a series of characterization 
tests that demonstrated the performance envelope of the modified hoist 
in various conditions. According to Collins Aerospace, the results of 
these tests as documented in Goodrich Report No. 49000-1087, Revision 
A, dated July 31, 2017, indicate that margins are maintained with a 
less restrictive temperature limitation than those imposed on non-
modified hoists.
    As the FAA explained in the SNPRM, the FAA disagrees with requiring 
different maximum hoist load limitations for non-modified hoists and 
modified hoists. After reviewing the data in the report referenced by 
the

[[Page 14774]]

commenter, the FAA determined it does not demonstrate with an 
acceptable level of confidence that less restrictive temperature 
limitations are appropriate for modified hoists.

Requests Regarding the Partial Peel Out Requirement

    In the SNPRM, the FAA proposed to prohibit use of the hoist if a 
partial peel out occurs, through both a placard limitation and a 
requirement to deactivate or remove the hoist. Bell Canada requested 
the FAA remove the proposed placard requirement because it only 
requires that the pilot cease using the hoist before the next flight 
and does not provide crew instructions to be executed during the hoist 
operation.
    The placard provides requirements for the crew following any 
partial peel out. The FAA determined that the most effective way to 
provide this information to the aircrew is through a placard.
    In the SNPRM, the FAA proposed to define partial peel out as 
occurring when 20 inches or more of the hoist cable reels off of the 
cable drum in one clutch slip incident. Bell Canada requested the FAA 
change this definition to ``approximately'' 20 inches. Bell Canada 
stated that a finite 20 inches will be difficult to measure; 
``approximately 20 inches'' would be consistent with the Goodrich 
service information.
    A measurement of ``approximately 20 inches'' would be vague in that 
it may be interpreted in more than one way. The operator is capable of 
measuring 20 or more inches of the hoist cable by, for example, using 
slippage markings on the cable.

Conclusion

    Affected helicopters include helicopters that have been approved by 
the aviation authorities of Canada, Italy, France, and Germany and are 
approved for operation in the United States. Pursuant to the FAA's 
bilateral agreement with the European Union, EASA has notified the FAA 
about the unsafe condition described in its AD. The FAA reviewed the 
relevant data, considered the comments received, and determined that 
air safety requires adopting this AD as proposed. Accordingly, the FAA 
is issuing this AD to address the unsafe condition on these products. 
Except for the changes described previously, this AD is adopted as 
proposed in the SNPRM. None of the changes will increase the economic 
burden on any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Goodrich Alert Service Bulletin No. ASB 44301-10-
18, Revision 6, dated October 10, 2016, which specifies maximum hoist 
load limitations with respect to ambient temperature and describes 
actions and conditions that could reduce the capacity of the clutch. 
This service information also specifies procedures for inspecting the 
cable and inspecting the clutch by performing a cable conditioning lift 
and a hoist slip load test.
    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.

Differences Between This AD and the EASA AD

    EASA AD 2015-0226R5 requires repetitively replacing the hoist with 
a modified hoist, whereas this AD requires a one-time replacement of 
the hoist with a modified hoist that has the improved clutch assembly 
installed. EASA AD 2015-0226R5 requires adding a placard or operational 
limitation to the RFM warning that exceeding 15[deg] of lateral 
pendulum angle/helicopter vertical axis can lead to clutch slippage, 
and this AD does not. EASA AD 2015-0226R5 requires adding an operating 
limitation to the RFM limiting the number of persons who can be 
hoisted, whereas this AD does not. This AD requires replacing the cable 
before the next hoist operation if a cable has previously been load-
tested at more than 1,500 lbs or at an unknown weight during at least 
one cable pull, while EASA AD 2015-0226R5 requires this replacement 
during multiple cable pulls. This AD requires visually inspecting and 
measuring the diameter of the cable before and after performing a cable 
conditioning and a hoist slip load test, whereas EASA AD 2015-0226R5 
does not. This AD requires performing the cable conditioning and hoist 
slip load test within 30 days after the effective date of this AD, 
unless already done within the last 6 calendar months, and thereafter 
at intervals not to exceed 6 months, 400 lifts, or 300 cycles. EASA AD 
2015-0226R5 specifies performing the hoist slip load test according to 
the compliance time of the design approval holder instead. After the 
installation (not reinstallation) of a modified hoist, EASA AD 2015-
0226R5 requires performing an initial hoist load check/test prior to 
hoisting operation, whereas this AD does not.

Interim Action

    The FAA considers this AD an interim action. The inspection reports 
required by this AD will enable better insight into the condition of 
the hoists, and eventually be used to develop final action to address 
the unsafe condition. Once final action has been identified, the FAA 
might consider further rulemaking.

Costs of Compliance

    The FAA estimates that this AD affects 2,911 hoists installed on 
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.
    Replacing a clutch takes about 8 work-hours and parts cost about 
$24,000 for an estimated cost of $24,680 per hoist. Alternatively, 
replacing a hoist takes about 8 work-hours and parts cost about 
$200,000 for an estimated cost of $200,680 per hoist.
    Revising the existing RFM for your helicopter and installing 
placards takes about 0.5 work-hour for an estimated cost of $43 per 
helicopter and $125,173 for the U.S. fleet.
    Deactivating or removing a hoist that experiences a partial peel 
out takes about 2 work-hours for an estimated cost of $170.
    Reviewing records takes about 0.5 work-hour for an estimated cost 
of $43 per helicopter and $125,173 for the U.S. fleet.
    Inspecting the cable and performing a cable conditioning lift and 
hoist slip load test takes about 2 work-hours for an estimated cost of 
$170 per helicopter and $494,870 for the U.S. fleet per inspection 
cycle. A load check tool costs about $11,171. Reporting the hoist slip 
load test information takes about 0.25 work-hour for a cost of $21 per 
helicopter and $61,131 for the U.S. fleet per reporting cycle.
    Replacing the cable takes about 3 work-hours and parts cost about 
$3,150 for a total replacement cost of $3,405 per hoist.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a currently valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of

[[Page 14775]]

information is estimated to take approximately 0.25 hour per response, 
including the time for reviewing instructions, searching existing data 
sources, gathering and maintaining the data needed, and completing and 
reviewing the collection of information. All responses to this 
collection of information are mandatory. Send comments regarding this 
burden estimate or any other aspect of this collection of information, 
including suggestions for reducing this burden to: Information 
Collection Clearance Officer, Federal Aviation Administration, 10101 
Hillwood Parkway, Fort Worth, TX 76177-1524.

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:

AD 2022-05-10 Goodrich Externally-Mounted Hoist Assemblies: 
Amendment 39-21962; Docket No. FAA-2020-1120; Project Identifier 
2019-SW-056-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective April 20, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to helicopters, certificated in any category, 
with an externally-mounted Goodrich hoist assembly (hoist) with a 
part number (P/N) or base P/N listed under the Hoist Family column 
in Table 1 of Goodrich Alert Service Bulletin No. 44301-10-18, 
Revision 6, dated October 10, 2016 (ASB 44301-10-18 Rev 6), 
installed. An affected hoist may be installed on but not limited to 
the following:

    Note 1 to the introductory text of paragraph (c):  The hoist P/N 
may be included as a component of a different part-numbered kit.

    (1) Airbus Helicopters (previously Eurocopter France) Model 
AS332L, AS332L1, AS332L2, AS350B2, AS350B3, AS365N3, and EC225LP 
helicopters;
    (2) Airbus Helicopters Deutschland GmbH (AHD) (previously 
Eurocopter Deutschland GmbH) Model EC135P1, EC135P2, EC135P2+, 
EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, MBB-BK 117 C-2, and 
MBB-BK 117 D-2 helicopters;
    (3) Bell Textron Canada Limited (previously Bell Helicopter 
Textron Canada Limited) Model 429 and 430 helicopters;
    (4) Bell Textron Inc. (previously Bell Helicopter Textron Inc.) 
Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters;
    (5) Leonardo S.p.a. (previously Finmeccanica S.p.A., 
AgustaWestland S.p.A) Model A109, A109A, A109A II, A109C, A109E, 
A109K2, A109S, AB139, AB412, AB412 EP, AW109SP, and AW139 
helicopters;
    (6) MD Helicopters, Inc. (MDHI) Model MD900 helicopters;
    (7) Transport and restricted category helicopters, originally 
manufactured by Sikorsky Aircraft Corporation, Models S-61A, S-61L, 
S-61N, S-76A, S-76B, S-76C, S-76D, and S-92A; and
    (8) Restricted category Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, 
UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 2500, Cabin 
Equipment/Furnishings.

(e) Unsafe Condition

    This AD was prompted by hoists failing lower load limit 
inspections. The FAA is issuing this AD to prevent failure of the 
hoist overload clutch. The unsafe condition, if not addressed, could 
result in an in-flight failure of the hoist, which could result in 
injury to a person being lifted.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For a hoist without the number ``4'' as the first digit of 
its serial number (S/N):
    (i) For hoists that use operating hours to monitor hoist 
operation, within 24 months after the effective date of this AD or 
before the hoist accumulates 55 total hoist operating hours, 
whichever occurs first, replace the hoist. For purposes of this AD, 
hoist operating hours are counted anytime the hoist motor is 
operating.
    (ii) For hoists that use hoist cycles (cycles) to monitor hoist 
operation, within 24 months after the effective date of this AD or 
before the hoist accumulates 1,200 total cycles, whichever occurs 
first, replace the hoist. For purposes of this AD, a cycle is 
counted anytime the cable is extended and then retracted a minimum 
of 16 feet (5 meters) during flight or on the ground, with or 
without a load.
    (iii) For hoists that use hoist lifts (lifts) to monitor hoist 
operation, within 24 months after the effective date of this AD or 
before the hoist accumulates 1,600 total lifts, whichever occurs 
first, replace the hoist. For purposes of this AD, a lift is counted 
anytime the cable is unreeled or recovered or both with a load 
attached to the hook, regardless of the length of the cable that is 
deployed or recovered. An unreeling or recovery of the cable with no 
load on the hook is not a lift. If a load is applied for half an 
operation (i.e. unreeling or recovery), it must be counted as one 
lift.
    (2) For all hoists identified in the introductory text of 
paragraph (c) of this AD, before further flight, install placards 
and revise the existing Rotorcraft Flight Manual (RFM) for your 
helicopter by inserting a copy of this AD or by making pen-and-ink 
changes in Section 2, Limitations, of the RFM Supplement for the 
hoist as follows:
    (i) For 500 pound (lb) rated hoists, install a placard with the 
information in Figure 1 to paragraph (g)(2)(i) of this AD in full 
view of the hoist operator and add the information in Figure 1 to 
paragraph (g)(2)(i) of this AD to the existing RFM for your 
helicopter.
BILLING CODE 4910-13-P

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[GRAPHIC] [TIFF OMITTED] TR16MR22.032


[[Page 14777]]


[GRAPHIC] [TIFF OMITTED] TR16MR22.033

BILLING CODE 4910-13-C
    (3) For all hoists identified in the introductory text of 
paragraph (c) of this AD, as of the effective date of this AD, if a 
partial peel out occurs, deactivate or remove the hoist from service 
before further flight. For purposes of this AD, a partial peel out 
occurs when 20 inches (0.5 meter) or more of the hoist cable reels 
off of the hoist cable drum in one overload clutch slip incident.
    (4) For all hoists identified in the introductory text of 
paragraph (c) of this AD, within 30 days after the effective date of 
this AD, review the helicopter's hoist slip load test records. If 
the cable was load-tested at more than 1,500 lbs or at an unknown 
weight during one or more cable pulls, replace the cable with an 
airworthy cable before the next hoist operation.
    (5) For all hoists identified in the introductory text of 
paragraph (c) of this AD, within 30 days after the effective date of 
this AD, unless already done within the last 6 calendar months, and 
thereafter at intervals not to exceed 6 months, 400 lifts, or 300 
cycles, whichever occurs first:
    (i) Visually inspect the first 18 inches (45 cm) of the cable 
from the hook assembly for broken wires and necked down sections. If 
there is a broken wire or necked down section, replace the cable 
with an airworthy cable before further flight.
    (ii) Within the first 18 inches (45 cm) of the cable from the 
hook assembly, measure the diameter of the cable at the most necked 
down area. If the diameter measurement is less than 0.185 inch (4.7 
mm), replace the cable with an airworthy cable before further 
flight.
    (iii) Using load check tool P/N 49900-889-103 or 49900-889-104, 
perform a cable conditioning and a hoist slip load test by following 
the Accomplishment Instructions, paragraphs 3.C.(1) through 
3.C.(3)(g) of ASB 44301-10-18 Rev 6. If the average of the five test 
values is less than the limit shown in Table 2 for 600 lb rated 
hoists or Table 3 for 500 lb rated hoists of ASB 44301-10-18 Rev 6, 
remove the hoist from service before further flight.
    (iv) Visually inspect the first 30 feet (10 meters) of the cable 
from the hook assembly for broken wires, necked down sections, 
kinks, bird-caging, flattened areas, abrasion, and gouging. It is 
permissible for the cable to have a slight curve immediately after 
performing the hoist slip load test. If there is a broken wire, 
necked down section, kink, or any bird-caging; or if there is a 
flattened area, any abrasion, or a gouge that exceeds allowable 
limits, replace the cable with an airworthy cable before further 
flight.
    (v) Repeat the actions specified in paragraphs (g)(5)(i) and 
(ii) of this AD. If there is a broken wire or necked down section or 
the cable diameter measurement is less than 0.185 inch (4.7 mm), 
replace the cable with an airworthy cable before further flight.
    (6) Within 30 days after accomplishing the hoist slip load test, 
report the information requested in Appendix 1 to this AD by email 
to [email protected]; or mail to Goodrich, Collins Aerospace; 
2727 E. Imperial Hwy., Brea, CA 92821.
    (7) As of the effective date of this AD, do not install as a 
replacement part or as an original installation an externally-
mounted hoist with a P/N identified in the introductory text of 
paragraph (c) of this AD unless it has an improved overload clutch 
assembly with the number ``4'' as the first digit of the S/N.

(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)(1) 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.

(i) Related Information

    (1) For more information about this AD, contact Kristi Bradley, 
Program Manager, COS Program Management Section, Operational Safety 
Branch, Compliance & Airworthiness Division, FAA, 10101 Hillwood 
Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email 
[email protected].
    (2) The subject of this AD is addressed in European Union 
Aviation Safety Agency (EASA) AD 2015-0226R5, Revision 5, dated July 
23, 2020. You may view the EASA AD at https://www.regulations.gov in 
Docket No. FAA-2020-1120.

(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) Goodrich Alert Service Bulletin No. 44301-10-18, Revision 6, 
dated October 10, 2016.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Collins Aerospace; 2727 E Imperial Hwy., Brea, CA 92821; telephone 
(714) 984-1461; email [email protected]; or at https://www.collinsaerospace.com/.
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Appendix 1 to AD 2022-05-10

Hoist Slip Load Test Results (sample format)

    Provide the following information by email to [email protected]; or mail to Goodrich, Collins Aerospace; 2727 E 
Imperial Hwy., Brea, CA 92821.

Helicopter Owner/Operator Name:
Email Address:
Telephone Number:
Helicopter Model and Serial Number:

[[Page 14778]]

Hoist Part Number:
Hoist Serial Number:
Time since Last Hoist Overhaul (months):
Hoist Operating Hours:
Hoist Cycles:
Hoist Lifts:
Date and Location Test was Accomplished:
Point of Contact for Additional Information:
Air Temperature:
Gearbox Lubricant:
Hoist Slip Load Test Value 1:
Hoist Slip Load Test Value 2:
Hoist Slip Load Test Value 3:
Hoist Slip Load Test Value 4:
Hoist Slip Load Test Value 5:
Hoist Slip Load Test Averaged Test Value:
Any notes or comments:

    Issued on February 23, 2022.
Derek Morgan,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-05487 Filed 3-15-22; 8:45 am]
BILLING CODE 4910-13-P


