[Federal Register Volume 86, Number 187 (Thursday, September 30, 2021)]
[Proposed Rules]
[Pages 54129-54135]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-21076]



[[Page 54129]]

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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]
RIN 2120-AA64


Airworthiness Directives; Goodrich Externally-Mounted Hoist 
Assemblies

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM).

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SUMMARY: The FAA is revising a notice of proposed rulemaking (NPRM) for 
various model helicopters with certain part-numbered Goodrich 
externally-mounted hoist assemblies (hoists) installed. This action 
revises the NPRM by adding a figure and revising certain requirements. 
The FAA is proposing this airworthiness directive (AD) to address the 
unsafe condition on these products. Since some of these actions would 
impose an additional burden over those in the NPRM, the agency is 
requesting comments on this SNPRM.

DATES: The FAA must receive comments on this SNPRM by November 1, 2021.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     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.
     Hand Delivery: Deliver to Mail address between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays.
    For Goodrich service information identified in this SNPRM, contact 
Collins Aerospace; 2727 E Imperial Hwy., Brea, CA 92821; telephone 
(714) 984-1461. 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 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 the NPRM, this SNPRM, 
the European Union Aviation Safety Agency (EASA) AD, any comments 
received, and other information. The street address for Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Kristi Bradley, Aerospace Engineer, 
General Aviation & Rotorcraft Section, International Validation Branch, 
Compliance & Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 76177; telephone (817) 222-5110; email 
kristin.bradley@faa.gov.

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-2020-1120; Project Identifier 
2019-SW-056-AD'' 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 again 
revise 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 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this proposed AD.

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 SNPRM 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 SNPRM, 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 SNPRM. Submissions containing CBI should 
be sent to Kristi Bradley, Aerospace Engineer, General Aviation & 
Rotorcraft Section, International Validation Branch, Compliance & 
Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone (817) 222-5110; email kristin.bradley@faa.gov. 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 an NPRM that proposed 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 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 FAA.
    The NPRM was prompted by a series of EASA ADs, the most recent 
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 advises 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 states 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 requires a records review to 
determine if the cable has 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 cannot 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

[[Page 54130]]

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 prohibits the 
installation of a replacement cable that has exceeded the allowable 
limit in previous load testing. EASA considers AD 2015-0226R5 to be 
interim action and advises further AD action may follow.

Comments

    The FAA received comments from three commenters. The commenters 
were EASA, Collins Aerospace, and an individual. The following 
discussion presents the comments received on the NPRM and the FAA's 
response.

Request To Clarify Interval Between Overhaul

    EASA requested the FAA clarify why the proposed AD does not include 
the reduced time interval between overhaul that is required by EASA's 
AD. EASA stated that based on the occurrences and design review, its AD 
limits the time between overhaul to 24 months, 1,200 cycles, or 1,600 
lifts, which can be extended to 40 months or 2,600 lifts if tests and 
documentation are provided to EASA.
    The FAA's proposed AD and EASA's AD differ in that the EASA AD 
requires repetitive replacement or overhaul of all affected hoists, 
while the FAA's proposed AD would require a one-time replacement of 
affected hoists that have not been modified with a new overload clutch 
assembly (and re-identified with a ``4'' as the first digit of the 
serial number (S/N)). Since the proposed AD would also prohibit 
installation of a hoist unless it has a ``4'' as the first digit of the 
S/N, this would have the effect of requiring replacement of a non-
modified hoist with a modified hoist. The FAA acquired data from 
Collins Aerospace that showed over 1,000 field load checks of hoists 
with a new overload clutch assembly with no reports of low pulling 
clutches or peel out events. The FAA evaluated this data and determined 
that it does not substantiate a 24-month repetitive replacement or 
overhaul of hoists that have been modified with the new overload clutch 
assembly. The FAA considers this AD action to be an interim action, and 
using the additional data reported following issuance of this AD, will 
re-evaluate this determination if needed.

Request Regarding Replacement of the Hoist

    One commenter requested the FAA allow installing a new clutch 
assembly instead of requiring ``scrapping'' the entire hoist, if the 
hoist does not have the number ``4'' as the first digit of its S/N.
    The FAA agrees. The requirement proposed by this AD to replace a 
hoist without the number ``4'' as the first digit of its S/N with a 
modified hoist would not require removing the hoist from service. The 
proposed requirement states to ``replace'' the hoist. This would not 
prohibit re-installing a hoist after modifying it to install a new 
overload clutch assembly and (re)-identifying it with a ``4'' as the 
first digit of the S/N. No changes to this proposed AD are necessary as 
a result of this comment.

Safety Concern Addressed by Existing AD

    One commenter stated that this clutch safety concern has already 
been addressed by AD 2013-06-51 (78 FR 38826, June 28, 2013) (AD 2013-
06-51), Goodrich Alert Service Bulletin (ASB) No. 44301-10-15, dated 
March 8, 2013 (ASB 44301-10-15), and Goodrich ASB No. 44301-10-18, 
Revision 6, dated October 10, 2016 (ASB 44301-10-18).
    The FAA agrees that ASB 44301-10-18 specifies procedures to address 
this issue. However, while an operator may incorporate the procedures 
in this service bulletin into its inspection program, not all operators 
are required to do so. In order for these procedures to become 
mandatory, and to correct the unsafe condition identified in the NPRM, 
the FAA must issue an AD. Further, AD 2013-06-51 (and ASB 44301-10-15, 
which is mandated by AD 2013-06-51) requires a one-time cable 
conditioning lift and load inspection test as interim corrective 
action. AD 2013-06-51 does not require all of the same actions as this 
proposed AD.

Requests Regarding Compliance Time for Hoist Replacement

    The individual commenter requested that the FAA change part of the 
compliance time for replacing a hoist without the number ``4'' as the 
first digit of its S/N from 55 operating hours to 55 hours since the 
last clutch overhaul. The commenter's hoist has 89 operating hours and 
was overhauled 2 hours ago; the commenter's understanding is that such 
a hoist would need to be replaced immediately when the proposed AD 
becomes effective.
    The FAA disagrees. If the commenter's hoist has an S/N without the 
number ``4'' as the first digit, then at its recent overhaul it was not 
modified with a new overload clutch assembly. Thus, it is still subject 
to the unsafe condition. Operators in this situation may, under the 
provisions of paragraph (h) of this SNPRM, request approval of an 
alternative method of compliance (AMOC) if sufficient data is submitted 
to substantiate an acceptable level of safety.
    Collins Aerospace stated that the compliance time for converting a 
hoist to a hoist with a new overload clutch assembly should be 24 
months, based on improved risk analysis information from initial load 
checks and subsequent load checks.
    The FAA partially agrees. The FAA also determined that 24 months is 
an adequate compliance time to mitigate the risk to reasonable levels. 
However, the FAA proposed a 12-month compliance time after factoring an 
estimated 12-month processing time before issuance of the final rule of 
this AD. The FAA did not make any changes to the SNPRM as a result of 
these comments.

Requests Regarding the Operating Limitations

    EASA requested the FAA explain why it did not adopt two of the 
operating limitations required by EASA AD 2015-0226R5: The limit on the 
number of persons that can be hoisted, and the warning that exceeding 
15[deg] of lateral pendulum angle/helicopter vertical axis may lead to 
clutch slippage.
    EASA AD 2015-0226R5 limits the number of persons that can be 
hoisted to two, except when hoisting more persons (such as children) 
will not exceed the weight limit. The FAA determined that the maximum 
hoist load limitations described in terms of weight alone, without the 
extraneous information on the number of persons lifted, are sufficient. 
The FAA did not propose to include the lateral pendulum angle of the 
hoist cable with respect to the helicopter's vertical axis after 
determining that such a limitation would not be measurable or 
enforceable. The FAA did not make any changes to the SNPRM as a result 
of this comment.
    EASA requested the FAA explain why the proposed AD would require 
different temperature ranges for the weight limitations than EASA AD 
2015-0226R5 and would omit limitations for OAT below -20 [deg]C.
    The FAA agrees that the maximum hoist load limitations in this 
proposed AD should be consistent with those in the EASA AD and that 
this proposed AD should include requirements for all temperatures. 
Accordingly, the FAA has changed the temperatures in the

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

Request To Allow Additional Load Check Tool

    Collins Aerospace requested the FAA change the proposed requirement 
to use load check tool P/N 49900-889-104 for the cable conditioning and 
a hoist slip load test to also allow using tool P/N 49900-889-103. 
Collins Aerospace stated that both are tool kits, with P/N 49900-889-
104 having all of the components of P/N 49900-889-103, plus extra 
components so that P/N 49900-889-104 can be used to perform tests on 
helicopters with older versions of the large hook damper. Collins 
Aerospace further stated that helicopters with newer model dampers and 
all other platforms can utilize tool P/N 49900-889-103, which is 
expected to supersede tool P/N 49900-889-104 as the older dampers are 
removed from service.
    The FAA agrees and has revised this SNPRM accordingly.

Request Regarding Hoist Load Check (Test) After Installation

    EASA requested the FAA explain why the proposed AD does not require 
accomplishing a hoist load check (test) after installing a new clutch, 
as required by the EASA AD. EASA stated the test will check for any 
uncertainties that might develop during handling and storage before 
installation.
    The FAA is not aware of any modified hoists with a new clutch 
(having a number ``4'' as the first digit of the S/N) failing the hoist 
load test. Accordingly, the FAA determined there is insufficient data 
to support proposing this as an additional requirement.

Request Regarding Compliance Time for Initial Load Test

    Collins Aerospace requested that, for certain hoists, the FAA 
extend the compliance time for the initial hoist slip load test from 30 
days to six months. In support of this request, Collins Aerospace 
stated the 30 day compliance time calculation is appropriate for non-
modified hoists that have: No improvements from manufacture, repair, or 
overhaul after February 1, 2018; not complied with ASB 44301-10-18 or 
ASB 44301-10-15; or not had a load check performed. Collins Aerospace 
further stated that enough load check tools may not be available to 
test all hoists that would be affected by the proposed AD.
    The FAA disagrees with changing the proposed AD to account for 
manufacturing improvements because not enough data has been provided to 
substantiate the commenter's request. However, the FAA agrees with 
providing an allowance for the initial instance of the cable 
inspections and hoist slip load test proposed by this AD if those 
actions have been accomplished within the last six months. The FAA has 
changed the proposed compliance time accordingly.

Request Regarding the Costs of Compliance

    Collins Aerospace stated that replacing a hoist is not necessary as 
the clutch can be replaced instead for an average cost of $24,000, plus 
8 hours of labor. Collins Aerospace also stated that the cost for the 
field load check tool is $11,171.
    The FAA agrees that replacing a hoist without the number ``4'' as 
the first digit of its S/N, as required by paragraph (g)(1) of this 
SNPRM, may be accomplished by modifying the hoist with the new overload 
clutch assembly and re-identifying it with a
    ``4'' as the first digit of the S/N. The FAA has updated the Costs 
of Compliance section accordingly.

Comment Regarding Figure 4

    Collins Aerospace stated that although a figure 4 is referenced in 
the Required Actions of the NPRM, no figure 4 appears in the NPRM.
    The FAA agrees. Figure 4 to paragraph (e)(2)(iv) of the NPRM (now 
Figure 4 to paragraph (g)(2)(iv) of this SNPRM), which is necessary to 
accomplish the required actions, was inadvertently omitted in 
reproduction when the NPRM published in the Federal Register.

Other Differences Between the NPRM and the SNPRM

    In this SNPRM, the FAA has added ``total'' to the compliance time 
and usage thresholds for hoists without a ``4'' as the first digit of 
its S/N to clarify that it is the total accumulation of time on the 
hoist that would trigger the proposed requirement to replace the hoist. 
In this SNPRM, the FAA has also added the metric conversion (kg) for 
the hoist ratings in the first two figures.
    Lastly, this SNPRM uses an updated format. As a result, paragraph 
identifiers have changed.

FAA's Determination

    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 is issuing this 
SNPRM after determining the unsafe condition described previously is 
likely to exist or develop on other helicopters of the same type 
design. Certain changes described above expand the scope of the NPRM. 
As a result, it is necessary to reopen the comment period to provide 
additional opportunity for the public to comment on this SNPRM.

Related Service Information Under 1 CFR part 51

    The FAA reviewed ASB 44301-10-18, 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.

Proposed AD Requirements in This SNPRM

    This proposed AD would require:
     Replacing any hoist without a ``4'' as the first digit of 
its S/N within 12 months after the effective date of this AD or before 
the hoist accumulates 55

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total operating hours, 1,200 total hoist cycles (cycles), or 1,600 
total hoist lifts (lifts), whichever occurs first.
     Installing placards and revising the existing RFM for your 
helicopter to add maximum hoist load limitations, an excessive 
maneuvering warning, a maximum sustained bank angle in turn, and a 
prohibition on operating the hoist in the event of a partial peel out.
     Deactivating or removing any hoist that experiences a 
partial peel out from service.
     Reviewing records for cable load-testing that was 
previously performed, and depending on the findings, replacing the 
cable.
     Repetitively inspecting the cable, inspecting the clutch 
by performing a cable conditioning lift and hoist slip load test, 
inspecting the cable a second time, reporting certain information to 
the FAA, and depending on these inspection outcomes, replacing the 
cable or removing the hoist from service.
    This proposed AD would also prohibit installing an affected 
replacement or original installation hoist that has not been re-
identified to indicate it has an improved clutch assembly.
    Installation of a hoist with an improved overload clutch assembly, 
which is indicated by having a ``4'' as the first digit of its S/N, 
would not terminate the actions required by this proposed AD.

Differences Between This SNPRM and the EASA AD

    EASA AD 2015-0226R5 requires repetitively replacing the hoist with 
a modified hoist, whereas this proposed AD would require 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 proposed AD would not. EASA AD 2015-0226R5 
requires adding an operating limitation to the RFM limiting the number 
of persons who can be hoisted, whereas this proposed AD would not. This 
proposed AD would require 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 proposed AD would require 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 
proposed AD would require 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 proposed AD would not.

Interim Action

    The FAA considers this proposed AD would be an interim action. The 
inspection reports that would be required by this proposed 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, if adopted as proposed, would 
affect 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 proposed AD.
    Replacing a clutch would take about 8 work-hours and parts would 
cost about $24,000 for an estimated cost of $24,680 per hoist. 
Alternatively, replacing a hoist would take about 8 work-hours and 
parts would cost about $200,000 for an estimated cost of $200,680 per 
hoist.
    Revising the existing RFM for your helicopter and installing 
placards would take 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 would take about 2 work-hours for an estimated cost of $170.
    Reviewing records would take 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 would take about 2 work-hours for an estimated 
cost of $170 per helicopter and $494,870 for the U.S. fleet per 
inspection cycle. A (field) load check tool would cost about $11,171. 
Reporting the hoist slip load test information would take 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 would take about 3 work-hours and parts would 
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 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 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

    The FAA determined that this proposed AD would not have federalism

[[Page 54133]]

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 adding the following new airworthiness 
directive:

Goodrich Externally-Mounted Hoist Assemblies: Docket No. FAA-2020-
1120; Project Identifier 2019-SW-056-AD.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by November 1, 2021.

(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 12 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 12 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 12 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:
[GRAPHIC] [TIFF OMITTED] TP30SE21.000

    (ii) For 600 lb rated hoists, install a placard with the 
information in Figure 2 to paragraph (g)(2)(ii) of this AD in full 
view of the hoist operator and add the information in Figure 2 to 
paragraph (g)(2)(ii) of this AD to the existing RFM for your 
helicopter:

[[Page 54134]]

[GRAPHIC] [TIFF OMITTED] TP30SE21.001

    (iii) For 500 and 600 lb rated hoists, install a placard with 
the information in Figure 3 to paragraph (g)(2)(iii) of this AD in 
full view of the pilot and add the information in Figure 3 to 
paragraph (g)(2)(iii) of this AD to the existing RFM for your 
helicopter.
[GRAPHIC] [TIFF OMITTED] TP30SE21.002

    (iv) For 500 and 600 lb rated hoists, install a placard with the 
information in Figure 4 to paragraph (g)(2)(iv) of this AD in full 
view of the pilot and add the information in Figure 4 to paragraph 
(g)(2)(iv) of this AD to the existing RFM for your helicopter:
[GRAPHIC] [TIFF OMITTED] TP30SE21.003

    (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 ASB.SIS-CA@utas.utc.com; or mail to Goodrich, Collins Aerospace; 
2727 E Imperial Hwy., Brea, CA 92821.

[[Page 54135]]

    (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: 9-AVS-AIR-730-AMOC@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

    (1) For more information about this AD, contact Kristi Bradley, 
Aerospace Engineer, General Aviation & Rotorcraft Section, 
International Validation Branch, Compliance & Airworthiness 
Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 
(817) 222-5110; email kristin.bradley@faa.gov.
    (2) For Goodrich service information identified in this AD, 
contact Collins Aerospace; 2727 E Imperial Hwy., Brea, CA 92821; 
telephone (714) 984-1461. 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.
    (3) 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 on the internet at https://www.regulations.gov in Docket No. FAA-2020-1120.

Appendix 1 to AD ####-##-##

Hoist Slip Load Test Results (Sample Format)

    Provide the following information by email to ASB.SIS-CA@utas.utc.com; 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:

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 September 22, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-21076 Filed 9-29-21; 8:45 am]
BILLING CODE 4910-13-P


