Airworthiness Directives; Various Restricted Category Helicopters, 3176-3182 [2022-00991]
Download as PDF
<![CDATA[
3176
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
B. Regulatory Impact Analysis:
E.O.12866
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
The MSPB has determined that this is
not a significant regulatory action under
E.O. 12866. Therefore, no regulatory
impact analysis is required.
C. Regulatory Flexibility Act
The Regulatory Flexibility Act (RFA)
requires an agency to prepare a
regulatory flexibility analysis for rules
unless the agency certifies that the rule
will not have a significant economic
impact on a substantial number of small
entities. The RFA applies only to rules
for which an agency is required to first
publish a proposed rule. See 5 U.S.C.
603(a) and 604(a). As discussed above,
the 2015 Act does not require agencies
to first publish a proposed rule when
adjusting CMPs within their
jurisdiction. Thus, the RFA does not
apply to this final rule.
D. Paperwork Reduction Act
This document does not contain
information collection requirements
subject to the Paperwork Reduction Act
of 1995, Public Law 104–13 (44 U.S.C.
Chapter 35).
E. Congressional Review Act
Pursuant to the Congressional Review
Act (5 U.S.C. 801, et seq.), the Office of
Information and Regulatory Affairs
designated this rule as not a ‘‘major
rule’’ as defined by 5 U.S.C. 804(2).
List of Subjects in 5 CFR Part 1201
Administrative practice and
procedure, Civil rights, Government
employees.
For the reasons set forth above, 5 CFR
part 1201 is amended as follows:
PART 1201—PRACTICES AND
PROCEDURES
1. The authority citation for part 1201
continues to read as follows:
■
Authority: 5 U.S.C. 1204, 1305, and 7701,
and 38 U.S.C. 4331, unless otherwise noted.
§ 1201.126
[Amended]
2. Section 1201.126 is amended in
paragraph (a) by removing ‘‘$1,125’’ and
adding in its place ‘‘$1,195.’’
jspears on DSK121TN23PROD with RULES1
■
Jennifer Everling,
Acting Clerk of the Board.
[FR Doc. 2022–01122 Filed 1–20–22; 8:45 am]
BILLING CODE 7401–01–P
VerDate Sep<11>2014
16:23 Jan 20, 2022
Jkt 256001
14 CFR Part 39
[Docket No. FAA–2021–0189; Project
Identifier AD–2020–00645–R; Amendment
39–21875; AD 2021–26–16]
RIN 2120–AA64
Airworthiness Directives; Various
Restricted Category Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
type certificated Model UH–1H
restricted category helicopters. This AD
was prompted by multiple reports of
failure of the main driveshaft. This AD
requires establishing a limit to replace
certain main driveshafts, and a one-time
and repetitive inspections of the main
driveshafts. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective February 25,
2022.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 25, 2022.
ADDRESSES: For service information
identified in this final rule, contact U.S.
Army Materiel Command Logistics Data
Analysis Center (USAMC LDAC),
ATTN: Equipment Publication Control
Officers (EPCOs), Building 3305, Redeye
Road, Redstone Arsenal, AL
35898–7466; telephone (256) 955–7716
or 1–866–211–3367; email
usarmy.redstone.ldac.mbx.logetm@
mail.mil; or at https://
enterprise.armyerp.army.mil.
You may also contact the following as
applicable:
Arrow Falcon Exporters Inc., 2081 S
Wildcat Way, Porterville, CA 93257;
telephone (559) 781–8604; fax (559)
781–9271; email afe@arrowfalcon.com.
Global Helicopter Technology, Inc.,
P.O. Box 180681, Arlington, Texas
76096; telephone (817) 557–3391; email
ghti@ghti.net.
Hagglund Helicopters, LLC, 5101 NW
A Avenue, Pendleton, OR 97801;
telephone (800) 882–3554 or (541)
276–3554; fax (541) 276–1597.
JASPP Engineering Services, LLC.,
511 Harmon Terrace, Arlington, TX
76010; telephone (817) 465–4495; or at
www.jjaspp.com.
Northwest Rotorcraft, LLC, 1000 85th
Ave. SE, Olympia, WA 98501; telephone
(360) 754–7200; or at
www.nwhelicopters.com.
SUMMARY:
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
Overseas Aircraft Support, Inc., P.O.
Box 898, Lakeside, AZ 85929; telephone
(928) 368–6965; fax (928) 368–6962.
Richards Heavylift Helo, Inc., 1181
Osprey Nest Point, Orange Park, FL
32073; (904) 472–1481; email
Glenn7444@msn.com.
Rotorcraft Development Corporation,
P.O. Box 430, Corvallis, MT 59828;
telephone (207) 329–2518; email
administration@
rotorcraftdevelopment.com.
Southwest Florida Aviation
International, Inc., 28000–A9 Airport
Road, Bldg. 101, Punta Gorda, FL
33982–9587; telephone (941) 637–1161;
fax (941) 637–6264; email info@
swfateam.org.
Tamarack Helicopters, Inc., 2849
McIntyre Rd., Stevensville, MT 59870;
telephone (406) 777–0144; or at
www.tamarackhelicopters.com.
You may view the 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. Service
information that is incorporated by
reference is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0189.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0189; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
final rule, any comments received, and
other information. The address for
Docket Operations is U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Ameet Shrotriya, Aerospace Engineer,
Delegation Oversight Section, DSCO
Branch, Compliance & Airworthiness
Division, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817)
222–5525; email ameet.shrotriya@
faa.gov.
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 restricted category Model
UH–1H helicopters with KAflex main
driveshaft part number (P/N)
SKCP2180–1, SKCP2281–1,
E:\FR\FM\21JAR1.SGM
21JAR1
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
SKCP2281–1R, or SKCP2281–103
installed. The NPRM published in the
Federal Register on March 26, 2021 (86
FR 16126). The NPRM was prompted by
multiple reports of failure of a main
driveshaft. In the NPRM, the FAA
proposed to require establishing a life
limit for those part-numbered main
driveshafts, removing and inspecting
the main driveshaft, inspecting the
alignment of the main driveshaft
installation, and repetitive inspections
of the main driveshaft. As an optional
terminating action, the NPRM proposed
to allow the installation of a certain
part-numbered main driveshaft not
affected by this unsafe condition. This
condition, if not addressed, could result
in loss of engine power to the
transmission and subsequent loss of
control of the helicopter.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
seven commenters. The commenters
were Kamatics Corporation; Northwest
Helicopters, LLC; Salmon River
Helicopters; and four individuals. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
jspears on DSK121TN23PROD with RULES1
Request Regarding the FAA’s
Justification of the Unsafe Condition
Salmon River Helicopters and two
individual commenters requested
information about the driveshaft failures
and one individual commenter asked if
the issue is unsafe.
The FAA utilized the FAA’s Service
Difficulty Reporting System (SDRS)
database,1 the National Transportation
Safety Board (NTSB) database,2 3
manufacturer reports of failures, and
other sources to identify seven failures.
The seven failures are: 891 Total hours
time-in-service (TIS) of the main
driveshaft, 1997, source: NTSB Accident
Number SEA97LA126; time in service
not identified, 2005, source: FAA
Service Difficult Report Unique Control
#2005FA0000785; 3341 total hours TIS
of the main driveshaft, 2007, source:
Manufacturer; 2432 total hours TIS of
the main driveshaft, 2010, source:
Manufacturer; 7598.6 total hours TIS
since last inspection, 2015, source
NTSB Accident Number WPR15LA178;
4353 total hours TIS of the main
driveshaft, 2016, source: Manufacturer;
1 https://av-info.faa.gov/sdrx/Query.aspx.
2 To search for NTSB cases in 2008 and previous,
go to: https://www.ntsb.gov/Pages/
AviationQuery.aspx.
3 To search for NTSB cases after 2008, go to:
https://data.ntsb.gov/carol-main-public/querybuilder.
VerDate Sep<11>2014
16:23 Jan 20, 2022
Jkt 256001
and time in service not identified, 2020,
source: Australian Transport Safety
Bureau. Based on recent review of
collected data, which factored in the
usage of the main driveshafts, the FAA
has determined that an unsafe condition
exists.
Requests Pertaining to the Applicability
An individual commenter asked for
information about main driveshaft P/Ns
SKCP2180–1 and SKCP2281–1R.
Main driveshaft P/Ns SKCP2180–1
and SKCP2281–1R are older P/Ns that
currently have approval for installation
in the domestic fleet and could be in
service. Those two P/Ns are included in
this AD due to design similarity and the
determination that they are affected by
the unsafe condition in this AD.
An individual commenter stated that
National Stock Number (NSN)
615–01–072–5670 is used for both main
driveshaft P/N CP2281–103, which is
affected by this AD, and main driveshaft
P/N SKCP3303–1, which is not affected
by this AD. The commenter asked how
main driveshaft P/N CP2281–103 is
affected by this AD and not main
driveshaft P/N SKCP3303–1 when,
according to the NSN, they are built to
the same standard.
An NSN is an identification label
assigned to an item or a group of similar
items, not limited to aircraft parts, and
is used for procurement purposes in the
Department of Defense (DOD) inventory.
An NSN provides a common
nomenclature of function, not a
standard, and is used in a catalog
system that is cross-compatible within
multiple agencies under DOD. A P/N is
assigned by the manufacturer. The
applicability of this AD is narrowed
down to any P/Ns that have an unsafe
condition. Main driveshaft P/N
SKCP3303–1 is an alternative part, and
the FAA does not have information
indicating that it is affected by the
unsafe condition in this AD.
Requests Regarding Overhauling a
Main Driveshaft
Northwest Helicopters, LLC, and an
individual commenter asked if the 5,000
total hours TIS removal is a retirement
life limit or an overhaul life limit. The
individual commenter requested that if
it is an overhaul life limit, the AD state
that KAflex main driveshaft P/N
SKCP2281–103 can be overhauled in
accordance with the US Army, Depot
Maintenance Work Requirement
(DMWR) 55–1615–278.
The FAA partially agrees. The FAA
agrees that a main driveshaft could be
overhauled. Accordingly, the
requirements proposed in paragraphs
(g)(1) and (2) of the NPRM to remove the
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
3177
main driveshaft from service have been
changed to replace the main driveshaft
in this final rule. Additionally,
clarification that the main driveshaft
may be overhauled has been added to
each instance to replace the main
driveshaft in the Required Actions
paragraph. The overhaul must be
accomplished by following FAAapproved procedures. U.S. Army
Aviation and Missile Command, DMWR
for Main Drive Shaft DMWR 55–1615–
278, Original Issuance, dated September
30, 2009 (DMWR 55–1615–278),
specifies procedures that are not FAAapproved. The FAA disagrees with
requiring DMWR 55–1615–278 to
accomplish an overhaul as it requires
specialized tooling to which owners/
operators may not have access.
Operators may, however, under the
provisions of paragraph (h) of this AD,
request approval of an alternative
method of compliance (AMOC) to use
DMWR 55–1615–278.
Kamatics Corporation stated that an
older main driveshaft can be rebuilt or
upgraded into main driveshaft P/N
SKCP3303–1 at a lower cost than
installing a new main driveshaft and
requested the FAA add this alternative
cost information.
The FAA agrees that some main
driveshafts could be overhauled into
main driveshaft P/N SKCP3303–1 and
has updated the Costs of Compliance
section accordingly.
Request Regarding Determining the
Total Hours TIS of the Main Driveshaft
Kamatics Corporation stated that
service hours for most of the fielded
main driveshafts is often not known and
an individual commenter asked what to
do if the proof of time since new on the
main drive shaft is not recorded in any
aircraft logs.
The FAA recognizes that this
situation could exist. In light of this, the
FAA has determined to require using
the helicopter’s total hours TIS if the
total hours TIS of the main driveshaft
cannot be determined.
Request To Restrict Accomplishment of
Certain AD Requirements
Kamatics Corporation requested the
AD require that any main driveshaft
teardown be accomplished by an FAAapproved facility. Kamatics Corporation
stated that inspection for wear within
critical bolt joints requires a teardown.
Kamatics Corporation stated that UH–
1H Technical Manual paragraph 6–24.5
of Change 13 states ‘‘do not attempt to
loosen or tighten any hardware (with
respect to the drive shaft).’’
The FAA disagrees. While the owner/
operator may choose to have the actions
E:\FR\FM\21JAR1.SGM
21JAR1
3178
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
required by this AD accomplished at an
approved repair station, a mechanic that
meets the requirements of 14 CFR part
65 subpart D is adequate to accomplish
the actions required by this AD.
Pertaining to paragraph 6–24.5 of the
UH–1H Technical Manual, this AD does
not require accomplishing the
procedures specified in paragraph 6–
24.5 of Headquarters, Department of the
Army, Aviation Unit and Intermediate
Maintenance Instructions Army Model
UH–1H/V/EH–1H/X Helicopters,
Technical Manual TM 55–1520–210–
23–1, Change No. 42, dated April 14,
2003 (TM 55–1520–210–23–1 Change
42).
jspears on DSK121TN23PROD with RULES1
Requests Pertaining to Certain Service
Information
An individual commenter requested
the FAA revise the AD so actions that
are required by following certain
procedures in TM 55–1520–210–23–1
Change 42, would be required using
Headquarters, Department of the Army,
Aviation Unit and Intermediate
Maintenance Instructions Army Model
UH–1H/V/EH–1H/X Helicopters,
Technical Manual TM 55–1520–210–
23–1, Change No. 47, dated September
20, 2005 (TM 55–1520–210–23–1
Change 47), instead because TM 55–
1520–210–23–1 Change 47 is the current
change.
The FAA agrees to allow TM 55–
1520–210–23–1 Change 47 as an option.
An individual commenter requested
the FAA revise the AD to reference U.S.
Army DMWR 55–1615–278 because this
service information provides inspection
and repair criteria for (main) driveshaft
P/N SKCP2281–103 once it has been
removed from the helicopter.
The FAA agrees. The FAA has
reviewed this service information and
added it to the Other Related Service
Information section.
Request To Require Removal of Certain
Part-Numbered Main Driveshafts From
Service
Kamatics Corporation requested the
FAA revise the AD to require removal
of main driveshaft P/Ns SKCP2180–1,
SKCP 2281–1, and SKCP2281–1R from
service. According to Kamatics
Corporation, those P/Ns were removed
from service by the U.S. Army due to
flex frame bolted joint deterioration.
The FAA disagrees because no data
has been provided to substantiate the
commenter’s request.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
VerDate Sep<11>2014
16:23 Jan 20, 2022
Jkt 256001
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, including updating the contact
information for the U.S. Army,
clarifying the specific portions of TM
55–1520–210–23–1 Change 42 that are
required to accomplish this Final rule,
and the changes described previously,
this AD is adopted as proposed in the
NPRM. None of the changes will
increase the economic burden on any
operator.
Related Service Information Under 1
CFR Part 51
The FAA reviewed ‘‘Figure 4–9.
Engine Air Inlet Filter Installation’’ on
page 4–16; page 4–17; ‘‘Figure 6–7.
Transmission Positioning for Driveshaft
Alignment’’ on page 6–2; ‘‘Figure 6–8.
Tool Application—Use of Alignment
Tool Set (T47)’’ on page 6–3; and pages
6–21 through 6–24, of TM 55–1520–
210–23–1 Change 42. This service
information contains main driveshaft
assembly figures and specifies
procedures for the main driveshaft
disassembly, and inspecting and
correction of its alignment.
The FAA also reviewed ‘‘Figure 4–9.
Engine Air Inlet Filter Installation’’ on
page 4–16; page 4–17; ‘‘Figure 6–7.
Transmission Positioning for Driveshaft
Alignment’’ on page 6–2; ‘‘Figure 6–8.
Tool Application—Use of Alignment
Tool Set (T47)’’ on page 6–3; pages 6–
21 through 6–24; and ‘‘Figure 6–12.2.
Main Driveshaft Installation & Removal
Tool’’ and ‘‘Figure 6–12.3. Work Aid
Tool Installed on Main Driveshaft’’ on
page 6–27, of TM 55–1520–210–23–1
Change 47. This service information
specifies the same procedures as TM
55–1520–210–23–1 Change 42 with
various updates throughout.
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 ADDRESSES.
Other Related Service Information
The FAA reviewed DMWR 55–1615–
278, for main driveshaft P/N
SKCP2281–103, which specifies
maintenance, overhaul, repair,
assembly, and balance procedures.
Costs of Compliance
The FAA estimates that this AD
affects 384 helicopters of U.S. registry.
Labor rates are estimated at $85 per
work-hour. Based on these numbers, the
FAA estimates that operators may incur
the following costs in order to comply
with this AD.
Determining the total hours TIS of the
main driveshaft takes about 0.5 work-
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
hour for an estimated cost of about $43
per helicopter and $16,512 for the U.S.
fleet. Removing and inspecting the main
driveshaft takes about 4 work-hours for
an estimated cost of $340 per helicopter
and $130,560 for the U.S. fleet.
Inspecting the installed main driveshaft
takes about 1 work-hour for an
estimated cost of about $85 per
helicopter and $32,640 for the U.S. fleet,
per inspection cycle. Inspecting the
alignment of the main driveshaft
installation takes about 2 work-hours for
an estimated cost of $170 per helicopter
and $65,280 for the U.S. fleet. If
required, adjusting the alignment takes
about 0.5 work-hour for an estimated
cost of $43 per instance. Replacing a
main driveshaft takes about 1 work-hour
and parts cost about $54,000, for an
estimated cost of $54,085 per
replacement. Alternatively, overhauling
a main driveshaft takes about 1 workhour for removal and reinstallation and
parts cost about $38,000, for an
estimated cost of $38,085 per overhaul.
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
E:\FR\FM\21JAR1.SGM
21JAR1
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
(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:
(d) Subject
Joint Aircraft System Component (JASC)
Code: 6310, Engine/Transmission Coupling.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2021–26–16 Various Restricted Category
Helicopters: Amendment 39–21875;
Docket No. FAA–2021–0189; Project
Identifier AD–2020–00645–R.
(a) Effective Date
This airworthiness directive (AD) is
effective February 25, 2022.
(b) Affected ADs
None.
jspears on DSK121TN23PROD with RULES1
(c) Applicability
This AD applies to restricted category
Model UH–1H helicopters; current type
certificate holders include but are not limited
to Arrow Falcon Exporters Inc.; Global
Helicopter Technology, Inc.; Hagglund
VerDate Sep<11>2014
16:23 Jan 20, 2022
Jkt 256001
Helicopters, LLC; JJASPP Engineering
Services, LLC.; Northwest Rotorcraft, LLC;
Overseas Aircraft Support, Inc.; Richards
Heavylift Helo, Inc.; Rotorcraft Development
Corporation; Southwest Florida Aviation
International, Inc.; and Tamarack
Helicopters, Inc., with KAflex main
driveshaft part number (P/N) SKCP2180–1,
SKCP2281–1, SKCP2281–1R, or SKCP2281–
103 installed.
Note 1 to paragraph (c): Helicopters with
an SW205 designation are Southwest Florida
Aviation International, Inc., Model UH–1H
helicopters.
(e) Unsafe Condition
This AD was prompted by multiple reports
of failure of the main driveshaft. The unsafe
condition, if not addressed, could result in
loss of engine power to the transmission 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 after the effective
date of this AD, determine the total hours
time-in-service (TIS) of the main driveshaft.
If the total hours TIS of the main driveshaft
cannot be determined, use the helicopter’s
total hours TIS as the total hours TIS of the
main driveshaft for the action required by
this paragraph.
(i) If the main driveshaft has accumulated
less than 5,000 total hours TIS, before
exceeding 5,000 total hours TIS, replace the
main driveshaft. The main driveshaft may be
overhauled in accordance with FAAapproved procedures to accomplish the
replacement required by this paragraph.
Note 2 to paragraph (g)(1)(i): This note
applies to paragraphs (g)(1)(i) and (ii), (g)(2),
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
3179
and (g)(3)(i) through (iv) of this AD. U.S.
Army Aviation and Missile Command, Depot
Maintenance Work Requirement for Main
Drive Shaft DMWR 55–1615–278, Original
Issuance, dated September 30, 2009, specifies
procedures that are not FAA-approved.
(ii) If the main driveshaft has accumulated
5,000 or more total hours TIS, before further
flight, replace the main driveshaft. The main
drive shaft may be overhauled in accordance
with FAA-approved procedures to
accomplish the replacement required by this
paragraph.
(2) Thereafter following paragraph (g)(1) of
this AD, replace the main driveshaft before
accumulating 5,000 total hours TIS. The
main drive shaft may be overhauled in
accordance with FAA-approved procedures
to accomplish the replacement required by
this paragraph.
(3) Within 25 hours TIS after the effective
date of this AD, remove main driveshaft P/
N SKCP2180–1, SKCP2281–1, SKCP2281–1R,
or SKCP2281–103 by following ‘‘6–24.3.
Removal—Main Driveshaft P/N SKCP2281–
103’’ on page 6–24, including ‘‘4–24.
Removal—Air Inlet Filters’’ on page 4–17 and
‘‘Figure 4–9. Engine Air Inlet Filter
Installation’’ on page 4–16, of Headquarters,
Department of the Army, Aviation Unit and
Intermediate Maintenance Instructions Army
Model UH–1H/V/EH–1H/X Helicopters,
Technical Manual TM 55–1520–210–23–1,
Change No. 42, dated April 14, 2003 (TM 55–
1520–210–23–1 C 42), except where
instructed to ‘‘refer to figure 6–12.2’’ in TM
55–1520–210–23–1 C 42, refer to Figure 1 to
the introductory text of paragraph (g)(3) of
this AD, and where instructed to ‘‘see figure
6–12.3’’ in TM 55–1520–210–23–1 C 42, see
Figure 2 to the introductory text of paragraph
(g)(3) of this AD, and:
Note 3 to the introductory text of
paragraph (g)(3): Figures 6–12.2 and 6–12.3
are missing from TM 55–1520–210–23–1 C
42.
E:\FR\FM\21JAR1.SGM
21JAR1
(i) Inspect for any broken, loose, or missing
hardware. If there is broken or loose
hardware, before further flight, remove the
main driveshaft from service. If there is
missing hardware, before further flight,
replace the main driveshaft. The main drive
shaft may be overhauled in accordance with
FAA-approved procedures to accomplish the
replacement required by this paragraph.
(ii) Visually inspect each flex frame and
mount bolt torque stripe (red or yellow) for
movement. If there is any torque stripe
movement, before further flight, replace the
main driveshaft. The main drive shaft may be
VerDate Sep<11>2014
16:23 Jan 20, 2022
Jkt 256001
overhauled in accordance with FAAapproved procedures to accomplish the
replacement required by this paragraph.
(iii) Visually inspect each joint for fretting
corrosion, which may be indicated by red
metallic particles. If there is any grease, oil,
or dirt covering a joint, clean the area and
visually inspect again. If there is any fretting
corrosion, before further flight, replace the
main driveshaft. The main drive shaft may be
overhauled in accordance with FAAapproved procedures to accomplish the
replacement required by this paragraph.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
(iv) Inspect the main driveshaft for
mechanical damage, corrosion, an edge dent,
and nick as shown in Figure 3 to paragraph
(g)(3)(iv) of this AD. For the purposes of this
inspection, mechanical damage may be
indicated by a crack, scratch, or wear; and
corrosion may be indicated by corrosion or
pitting. If there is a scratch, wear, corrosion,
pitting, an edge dent, or a nick within
allowable limits, before further flight, repair
the main driveshaft in accordance with FAAapproved procedures. If there is a crack, or
a scratch, wear, corrosion, pitting, an edge
dent, or a nick that exceeds allowable limits,
E:\FR\FM\21JAR1.SGM
21JAR1
ER21JA22.001</GPH>
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
ER21JA22.000</GPH>
jspears on DSK121TN23PROD with RULES1
3180
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
VerDate Sep<11>2014
16:23 Jan 20, 2022
Jkt 256001
approved procedures to accomplish the
replacement required by this paragraph.
PO 00000
Frm 00007
Fmt 4700
Sfmt 4725
E:\FR\FM\21JAR1.SGM
21JAR1
ER21JA22.002</GPH>
jspears on DSK121TN23PROD with RULES1
before further flight, replace the main
driveshaft. The main drive shaft may be
overhauled in accordance with FAA-
3181
3182
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations
jspears on DSK121TN23PROD with RULES1
(4) Before installing the main driveshaft
following paragraph (g)(3) of this AD, and
with the engine adapter installed in the end
of the engine output shaft, inspect the
alignment of the main driveshaft installation
between the transmission input drive quill
coupling and the engine output shaft adapter
by following ‘‘6–24. Alignment—Main
Driveshaft,’’ paragraphs c. through g. on
pages 6–21 through 6–23, including ‘‘Figure
6–7. Transmission Positioning for Driveshaft
Alignment’’ on page 6–2 (Figure 6–7), and
‘‘Figure 6–8. Tool Application—Use of
Alignment Tool Set (T47)’’ on page 6–3
(Figure 6–8), of TM 55–1520–210–23–1 C 42.
If there is misalignment, before further flight,
adjust the alignment by following ‘‘6–24.
Alignment—Main Driveshaft,’’ paragraphs h.
through j. on page 6–23, including Figure 6–
7 and Figure 6–8, of TM 55–1520–210–23–1
C 42.
(5) Within 300 hours TIS after the effective
date of this AD, and thereafter within
intervals not to exceed 300 hours TIS, with
the main driveshaft installed, accomplish the
actions in paragraphs (g)(3)(i) through (iv) of
this AD.
(6) As an optional terminating action for
the requirements of this AD, you may install
KAflex main driveshaft P/N SKCP3303–1.
(7) As an option to accomplishing the
actions by following the specified portions in
TM 55–1520–210–23–1 C 42 in paragraphs
(g)(3) and (4) of this AD, you may accomplish
the actions by following those specified
portions in Headquarters, Department of the
Army, Aviation Unit and Intermediate
Maintenance Instructions Army Model UH–
1H/V/EH–1H/X Helicopters, Technical
Manual TM 55–1520–210–23–1, Change No.
47, dated September 20, 2005 (TM 55–1520–
210–23–1 C 47), and disregard exceptions to
refer to Figure 1 and see Figure 2 to the
introductory text of paragraph (g)(3) of this
AD, instead refer to ‘‘Figure 6–12.2. Main
Driveshaft Installation & Removal Tool’’ and
see ‘‘Figure 6–12.3. Work Aid Tool Installed
on Main Driveshaft,’’ on page 6–27 of TM 55–
1520–210–23–1 C 47 as instructed in TM 55–
1520–210–23–1 C 47.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, DSCO 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 certification office,
send it to the attention of the person
identified in paragraph (i) of this AD.
Information may be emailed to: 9-ASW-190COS@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, Aerospace
Engineer, Delegation Oversight Section,
DSCO Branch, Compliance & Airworthiness
VerDate Sep<11>2014
16:23 Jan 20, 2022
Jkt 256001
Division, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222–5525;
email ameet.shrotriya@faa.gov.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) 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) Headquarters, Department of the Army,
Aviation Unit and Intermediate Maintenance
Instructions Army Model UH–1H/V/EH–1H/
X Helicopters, Technical Manual TM 55–
1520–210–23–1, Change No. 42, dated April
14, 2003:
(A) ‘‘Figure 4–9. Engine Air Inlet Filter
Installation,’’ page 4–16;
(B) Page 4–17;
(C) ‘‘Figure 6–7. Transmission Positioning
for Driveshaft Alignment,’’ page 6–2;
(D) ‘‘Figure 6–8. Tool Application—Use of
Alignment Tool Set (T47),’’ page 6–3; and
(E) Pages 6–21 through 6–24.
(ii) Headquarters, Department of the Army,
Aviation Unit and Intermediate Maintenance
Instructions Army Model UH–1H/V/EH–1H/
X Helicopters, Technical Manual TM 55–
1520–210–23–1, Change No. 47, dated
September 20, 2005:
(A) ‘‘Figure 4–9. Engine Air Inlet Filter
Installation,’’ page 4–16;
(B) Page 4–17;
(C) ‘‘Figure 6–7. Transmission Positioning
for Driveshaft Alignment,’’ page 6–2;
(D) ‘‘Figure 6–8. Tool Application—Use of
Alignment Tool Set (T47),’’ page 6–3;
(E) Pages 6–21 through 6–24; and
(F) ‘‘Figure 6–12.2. Main Driveshaft
Installation & Removal Tool’’ and ‘‘Figure 6–
12.3. Work Aid Tool Installed on Main
Driveshaft,’’ page 6–27.
(3) For service information identified in
this AD, contact U.S. Army Materiel
Command Logistics Data Analysis Center
(USAMC LDAC), ATTN: Equipment
Publication Control Officers (EPCOs),
Building 3305, Redeye Road, Redstone
Arsenal, AL 35898–7466; telephone (256)
955–7716 or 1–866–211–3367; email
usarmy.redstone.ldac.mbx.logetm@mail.mil;
or at https://enterprise.armyerp.army.mil.
(4) You may view this service information
at 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: fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022–00991 Filed 1–20–22; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0949; Project
Identifier AD–2021–00115–E; Amendment
39–21915; AD 2022–02–18]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
General Electric Company (GE) CF6–
80C2A1, CF6–80C2A2, CF6–80C2A3,
CF6–80C2A5, CF6–80C2A5F, and CF6–
80C2A8 model turbofan engines with an
installed left-hand rear mount link
assembly, part number (P/N)
1846M23G01. This AD was prompted
by the manufacturer reducing the life
limit for the affected left-hand rear
mount link assembly. This AD requires
revising the airworthiness limitations
section (ALS) of the existing engine
maintenance manual and the operator’s
existing approved continuous
airworthiness maintenance program
(CAMP). The FAA is issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
DATES:
This AD is effective February 25,
2022.
For service information
identified in this final rule, contact
General Electric Company, 1 Neumann
Way, Cincinnati, OH 45215; phone:
(513) 552–3272; email:
aviation.fleetsupport@ae.ge.com;
website: https://www.ge.com. You may
view this service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. 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–2021–
0949.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0949; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
final rule, any comments received, and
other information. The address for
Docket Operations is U.S. Department of
E:\FR\FM\21JAR1.SGM
21JAR1
]]>Agencies
[Federal Register Volume 87, Number 14 (Friday, January 21, 2022)]
[Rules and Regulations]
[Pages 3176-3182]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-00991]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0189; Project Identifier AD-2020-00645-R;
Amendment 39-21875; AD 2021-26-16]
RIN 2120-AA64
Airworthiness Directives; Various Restricted Category Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain type certificated Model UH-1H restricted category helicopters.
This AD was prompted by multiple reports of failure of the main
driveshaft. This AD requires establishing a limit to replace certain
main driveshafts, and a one-time and repetitive inspections of the main
driveshafts. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective February 25, 2022.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 25,
2022.
ADDRESSES: For service information identified in this final rule,
contact U.S. Army Materiel Command Logistics Data Analysis Center
(USAMC LDAC), ATTN: Equipment Publication Control Officers (EPCOs),
Building 3305, Redeye Road, Redstone Arsenal, AL 35898-7466; telephone
(256) 955-7716 or 1-866-211-3367; email
[email protected]; or at https://enterprise.armyerp.army.mil.
You may also contact the following as applicable:
Arrow Falcon Exporters Inc., 2081 S Wildcat Way, Porterville, CA
93257; telephone (559) 781-8604; fax (559) 781-9271; email
[email protected].
Global Helicopter Technology, Inc., P.O. Box 180681, Arlington,
Texas 76096; telephone (817) 557-3391; email [email protected].
Hagglund Helicopters, LLC, 5101 NW A Avenue, Pendleton, OR 97801;
telephone (800) 882-3554 or (541) 276-3554; fax (541) 276-1597.
JASPP Engineering Services, LLC., 511 Harmon Terrace, Arlington, TX
76010; telephone (817) 465-4495; or at www.jjaspp.com.
Northwest Rotorcraft, LLC, 1000 85th Ave. SE, Olympia, WA 98501;
telephone (360) 754-7200; or at www.nwhelicopters.com.
Overseas Aircraft Support, Inc., P.O. Box 898, Lakeside, AZ 85929;
telephone (928) 368-6965; fax (928) 368-6962.
Richards Heavylift Helo, Inc., 1181 Osprey Nest Point, Orange Park,
FL 32073; (904) 472-1481; email [email protected].
Rotorcraft Development Corporation, P.O. Box 430, Corvallis, MT
59828; telephone (207) 329-2518; email
[email protected].
Southwest Florida Aviation International, Inc., 28000-A9 Airport
Road, Bldg. 101, Punta Gorda, FL 33982-9587; telephone (941) 637-1161;
fax (941) 637-6264; email [email protected].
Tamarack Helicopters, Inc., 2849 McIntyre Rd., Stevensville, MT
59870; telephone (406) 777-0144; or at www.tamarackhelicopters.com.
You may view the 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. Service information that is
incorporated by reference is also available at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0189.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0189; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this final rule, any
comments received, and other information. The address for Docket
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Ameet Shrotriya, Aerospace Engineer,
Delegation Oversight Section, DSCO Branch, Compliance & Airworthiness
Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone
(817) 222-5525; 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 restricted category
Model UH-1H helicopters with KAflex main driveshaft part number (P/N)
SKCP2180-1, SKCP2281-1,
[[Page 3177]]
SKCP2281-1R, or SKCP2281-103 installed. The NPRM published in the
Federal Register on March 26, 2021 (86 FR 16126). The NPRM was prompted
by multiple reports of failure of a main driveshaft. In the NPRM, the
FAA proposed to require establishing a life limit for those part-
numbered main driveshafts, removing and inspecting the main driveshaft,
inspecting the alignment of the main driveshaft installation, and
repetitive inspections of the main driveshaft. As an optional
terminating action, the NPRM proposed to allow the installation of a
certain part-numbered main driveshaft not affected by this unsafe
condition. This condition, if not addressed, could result in loss of
engine power to the transmission and subsequent loss of control of the
helicopter.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from seven commenters. The commenters
were Kamatics Corporation; Northwest Helicopters, LLC; Salmon River
Helicopters; and four individuals. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Request Regarding the FAA's Justification of the Unsafe Condition
Salmon River Helicopters and two individual commenters requested
information about the driveshaft failures and one individual commenter
asked if the issue is unsafe.
The FAA utilized the FAA's Service Difficulty Reporting System
(SDRS) database,\1\ the National Transportation Safety Board (NTSB)
database,2 3 manufacturer reports of failures, and other
sources to identify seven failures. The seven failures are: 891 Total
hours time-in-service (TIS) of the main driveshaft, 1997, source: NTSB
Accident Number SEA97LA126; time in service not identified, 2005,
source: FAA Service Difficult Report Unique Control #2005FA0000785;
3341 total hours TIS of the main driveshaft, 2007, source:
Manufacturer; 2432 total hours TIS of the main driveshaft, 2010,
source: Manufacturer; 7598.6 total hours TIS since last inspection,
2015, source NTSB Accident Number WPR15LA178; 4353 total hours TIS of
the main driveshaft, 2016, source: Manufacturer; and time in service
not identified, 2020, source: Australian Transport Safety Bureau. Based
on recent review of collected data, which factored in the usage of the
main driveshafts, the FAA has determined that an unsafe condition
exists.
---------------------------------------------------------------------------
\1\ https://av-info.faa.gov/sdrx/Query.aspx.
\2\ To search for NTSB cases in 2008 and previous, go to:
https://www.ntsb.gov/Pages/AviationQuery.aspx.
\3\ To search for NTSB cases after 2008, go to: https://data.ntsb.gov/carol-main-public/query-builder.
---------------------------------------------------------------------------
Requests Pertaining to the Applicability
An individual commenter asked for information about main driveshaft
P/Ns SKCP2180-1 and SKCP2281-1R.
Main driveshaft P/Ns SKCP2180-1 and SKCP2281-1R are older P/Ns that
currently have approval for installation in the domestic fleet and
could be in service. Those two P/Ns are included in this AD due to
design similarity and the determination that they are affected by the
unsafe condition in this AD.
An individual commenter stated that National Stock Number (NSN)
615-01-072-5670 is used for both main driveshaft P/N CP2281-103, which
is affected by this AD, and main driveshaft P/N SKCP3303-1, which is
not affected by this AD. The commenter asked how main driveshaft P/N
CP2281-103 is affected by this AD and not main driveshaft P/N SKCP3303-
1 when, according to the NSN, they are built to the same standard.
An NSN is an identification label assigned to an item or a group of
similar items, not limited to aircraft parts, and is used for
procurement purposes in the Department of Defense (DOD) inventory. An
NSN provides a common nomenclature of function, not a standard, and is
used in a catalog system that is cross-compatible within multiple
agencies under DOD. A P/N is assigned by the manufacturer. The
applicability of this AD is narrowed down to any P/Ns that have an
unsafe condition. Main driveshaft P/N SKCP3303-1 is an alternative
part, and the FAA does not have information indicating that it is
affected by the unsafe condition in this AD.
Requests Regarding Overhauling a Main Driveshaft
Northwest Helicopters, LLC, and an individual commenter asked if
the 5,000 total hours TIS removal is a retirement life limit or an
overhaul life limit. The individual commenter requested that if it is
an overhaul life limit, the AD state that KAflex main driveshaft P/N
SKCP2281-103 can be overhauled in accordance with the US Army, Depot
Maintenance Work Requirement (DMWR) 55-1615-278.
The FAA partially agrees. The FAA agrees that a main driveshaft
could be overhauled. Accordingly, the requirements proposed in
paragraphs (g)(1) and (2) of the NPRM to remove the main driveshaft
from service have been changed to replace the main driveshaft in this
final rule. Additionally, clarification that the main driveshaft may be
overhauled has been added to each instance to replace the main
driveshaft in the Required Actions paragraph. The overhaul must be
accomplished by following FAA-approved procedures. U.S. Army Aviation
and Missile Command, DMWR for Main Drive Shaft DMWR 55-1615-278,
Original Issuance, dated September 30, 2009 (DMWR 55-1615-278),
specifies procedures that are not FAA-approved. The FAA disagrees with
requiring DMWR 55-1615-278 to accomplish an overhaul as it requires
specialized tooling to which owners/operators may not have access.
Operators may, however, under the provisions of paragraph (h) of this
AD, request approval of an alternative method of compliance (AMOC) to
use DMWR 55-1615-278.
Kamatics Corporation stated that an older main driveshaft can be
rebuilt or upgraded into main driveshaft P/N SKCP3303-1 at a lower cost
than installing a new main driveshaft and requested the FAA add this
alternative cost information.
The FAA agrees that some main driveshafts could be overhauled into
main driveshaft P/N SKCP3303-1 and has updated the Costs of Compliance
section accordingly.
Request Regarding Determining the Total Hours TIS of the Main
Driveshaft
Kamatics Corporation stated that service hours for most of the
fielded main driveshafts is often not known and an individual commenter
asked what to do if the proof of time since new on the main drive shaft
is not recorded in any aircraft logs.
The FAA recognizes that this situation could exist. In light of
this, the FAA has determined to require using the helicopter's total
hours TIS if the total hours TIS of the main driveshaft cannot be
determined.
Request To Restrict Accomplishment of Certain AD Requirements
Kamatics Corporation requested the AD require that any main
driveshaft teardown be accomplished by an FAA-approved facility.
Kamatics Corporation stated that inspection for wear within critical
bolt joints requires a teardown. Kamatics Corporation stated that UH-1H
Technical Manual paragraph 6-24.5 of Change 13 states ``do not attempt
to loosen or tighten any hardware (with respect to the drive shaft).''
The FAA disagrees. While the owner/operator may choose to have the
actions
[[Page 3178]]
required by this AD accomplished at an approved repair station, a
mechanic that meets the requirements of 14 CFR part 65 subpart D is
adequate to accomplish the actions required by this AD. Pertaining to
paragraph 6-24.5 of the UH-1H Technical Manual, this AD does not
require accomplishing the procedures specified in paragraph 6-24.5 of
Headquarters, Department of the Army, Aviation Unit and Intermediate
Maintenance Instructions Army Model UH-1H/V/EH-1H/X Helicopters,
Technical Manual TM 55-1520-210-23-1, Change No. 42, dated April 14,
2003 (TM 55-1520-210-23-1 Change 42).
Requests Pertaining to Certain Service Information
An individual commenter requested the FAA revise the AD so actions
that are required by following certain procedures in TM 55-1520-210-23-
1 Change 42, would be required using Headquarters, Department of the
Army, Aviation Unit and Intermediate Maintenance Instructions Army
Model UH-1H/V/EH-1H/X Helicopters, Technical Manual TM 55-1520-210-23-
1, Change No. 47, dated September 20, 2005 (TM 55-1520-210-23-1 Change
47), instead because TM 55-1520-210-23-1 Change 47 is the current
change.
The FAA agrees to allow TM 55-1520-210-23-1 Change 47 as an option.
An individual commenter requested the FAA revise the AD to
reference U.S. Army DMWR 55-1615-278 because this service information
provides inspection and repair criteria for (main) driveshaft P/N
SKCP2281-103 once it has been removed from the helicopter.
The FAA agrees. The FAA has reviewed this service information and
added it to the Other Related Service Information section.
Request To Require Removal of Certain Part-Numbered Main Driveshafts
From Service
Kamatics Corporation requested the FAA revise the AD to require
removal of main driveshaft P/Ns SKCP2180-1, SKCP 2281-1, and SKCP2281-
1R from service. According to Kamatics Corporation, those P/Ns were
removed from service by the U.S. Army due to flex frame bolted joint
deterioration.
The FAA disagrees because no data has been provided to substantiate
the commenter's request.
Conclusion
The FAA reviewed the relevant data, considered any 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 minor editorial changes,
including updating the contact information for the U.S. Army,
clarifying the specific portions of TM 55-1520-210-23-1 Change 42 that
are required to accomplish this Final rule, and the changes described
previously, this AD is adopted as proposed in the NPRM. None of the
changes will increase the economic burden on any operator.
Related Service Information Under 1 CFR Part 51
The FAA reviewed ``Figure 4-9. Engine Air Inlet Filter
Installation'' on page 4-16; page 4-17; ``Figure 6-7. Transmission
Positioning for Driveshaft Alignment'' on page 6-2; ``Figure 6-8. Tool
Application--Use of Alignment Tool Set (T47)'' on page 6-3; and pages
6-21 through 6-24, of TM 55-1520-210-23-1 Change 42. This service
information contains main driveshaft assembly figures and specifies
procedures for the main driveshaft disassembly, and inspecting and
correction of its alignment.
The FAA also reviewed ``Figure 4-9. Engine Air Inlet Filter
Installation'' on page 4-16; page 4-17; ``Figure 6-7. Transmission
Positioning for Driveshaft Alignment'' on page 6-2; ``Figure 6-8. Tool
Application--Use of Alignment Tool Set (T47)'' on page 6-3; pages 6-21
through 6-24; and ``Figure 6-12.2. Main Driveshaft Installation &
Removal Tool'' and ``Figure 6-12.3. Work Aid Tool Installed on Main
Driveshaft'' on page 6-27, of TM 55-1520-210-23-1 Change 47. This
service information specifies the same procedures as TM 55-1520-210-23-
1 Change 42 with various updates throughout.
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 ADDRESSES.
Other Related Service Information
The FAA reviewed DMWR 55-1615-278, for main driveshaft P/N
SKCP2281-103, which specifies maintenance, overhaul, repair, assembly,
and balance procedures.
Costs of Compliance
The FAA estimates that this AD affects 384 helicopters of U.S.
registry. Labor rates are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates that operators may incur the following
costs in order to comply with this AD.
Determining the total hours TIS of the main driveshaft takes about
0.5 work-hour for an estimated cost of about $43 per helicopter and
$16,512 for the U.S. fleet. Removing and inspecting the main driveshaft
takes about 4 work-hours for an estimated cost of $340 per helicopter
and $130,560 for the U.S. fleet. Inspecting the installed main
driveshaft takes about 1 work-hour for an estimated cost of about $85
per helicopter and $32,640 for the U.S. fleet, per inspection cycle.
Inspecting the alignment of the main driveshaft installation takes
about 2 work-hours for an estimated cost of $170 per helicopter and
$65,280 for the U.S. fleet. If required, adjusting the alignment takes
about 0.5 work-hour for an estimated cost of $43 per instance.
Replacing a main driveshaft takes about 1 work-hour and parts cost
about $54,000, for an estimated cost of $54,085 per replacement.
Alternatively, overhauling a main driveshaft takes about 1 work-hour
for removal and reinstallation and parts cost about $38,000, for an
estimated cost of $38,085 per overhaul.
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
[[Page 3179]]
(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:
2021-26-16 Various Restricted Category Helicopters: Amendment 39-
21875; Docket No. FAA-2021-0189; Project Identifier AD-2020-00645-R.
(a) Effective Date
This airworthiness directive (AD) is effective February 25,
2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to restricted category Model UH-1H helicopters;
current type certificate holders include but are not limited to
Arrow Falcon Exporters Inc.; Global Helicopter Technology, Inc.;
Hagglund Helicopters, LLC; JJASPP Engineering Services, LLC.;
Northwest Rotorcraft, LLC; Overseas Aircraft Support, Inc.; Richards
Heavylift Helo, Inc.; Rotorcraft Development Corporation; Southwest
Florida Aviation International, Inc.; and Tamarack Helicopters,
Inc., with KAflex main driveshaft part number (P/N) SKCP2180-1,
SKCP2281-1, SKCP2281-1R, or SKCP2281-103 installed.
Note 1 to paragraph (c): Helicopters with an SW205 designation
are Southwest Florida Aviation International, Inc., Model UH-1H
helicopters.
(d) Subject
Joint Aircraft System Component (JASC) Code: 6310, Engine/
Transmission Coupling.
(e) Unsafe Condition
This AD was prompted by multiple reports of failure of the main
driveshaft. The unsafe condition, if not addressed, could result in
loss of engine power to the transmission 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 after the effective date of this AD,
determine the total hours time-in-service (TIS) of the main
driveshaft. If the total hours TIS of the main driveshaft cannot be
determined, use the helicopter's total hours TIS as the total hours
TIS of the main driveshaft for the action required by this
paragraph.
(i) If the main driveshaft has accumulated less than 5,000 total
hours TIS, before exceeding 5,000 total hours TIS, replace the main
driveshaft. The main driveshaft may be overhauled in accordance with
FAA-approved procedures to accomplish the replacement required by
this paragraph.
Note 2 to paragraph (g)(1)(i): This note applies to paragraphs
(g)(1)(i) and (ii), (g)(2), and (g)(3)(i) through (iv) of this AD.
U.S. Army Aviation and Missile Command, Depot Maintenance Work
Requirement for Main Drive Shaft DMWR 55-1615-278, Original
Issuance, dated September 30, 2009, specifies procedures that are
not FAA-approved.
(ii) If the main driveshaft has accumulated 5,000 or more total
hours TIS, before further flight, replace the main driveshaft. The
main drive shaft may be overhauled in accordance with FAA-approved
procedures to accomplish the replacement required by this paragraph.
(2) Thereafter following paragraph (g)(1) of this AD, replace
the main driveshaft before accumulating 5,000 total hours TIS. The
main drive shaft may be overhauled in accordance with FAA-approved
procedures to accomplish the replacement required by this paragraph.
(3) Within 25 hours TIS after the effective date of this AD,
remove main driveshaft P/N SKCP2180-1, SKCP2281-1, SKCP2281-1R, or
SKCP2281-103 by following ``6-24.3. Removal--Main Driveshaft P/N
SKCP2281-103'' on page 6-24, including ``4-24. Removal--Air Inlet
Filters'' on page 4-17 and ``Figure 4-9. Engine Air Inlet Filter
Installation'' on page 4-16, of Headquarters, Department of the
Army, Aviation Unit and Intermediate Maintenance Instructions Army
Model UH-1H/V/EH-1H/X Helicopters, Technical Manual TM 55-1520-210-
23-1, Change No. 42, dated April 14, 2003 (TM 55-1520-210-23-1 C
42), except where instructed to ``refer to figure 6-12.2'' in TM 55-
1520-210-23-1 C 42, refer to Figure 1 to the introductory text of
paragraph (g)(3) of this AD, and where instructed to ``see figure 6-
12.3'' in TM 55-1520-210-23-1 C 42, see Figure 2 to the introductory
text of paragraph (g)(3) of this AD, and:
Note 3 to the introductory text of paragraph (g)(3): Figures 6-
12.2 and 6-12.3 are missing from TM 55-1520-210-23-1 C 42.
[[Page 3180]]
[GRAPHIC] [TIFF OMITTED] TR21JA22.000
[GRAPHIC] [TIFF OMITTED] TR21JA22.001
(i) Inspect for any broken, loose, or missing hardware. If there
is broken or loose hardware, before further flight, remove the main
driveshaft from service. If there is missing hardware, before
further flight, replace the main driveshaft. The main drive shaft
may be overhauled in accordance with FAA-approved procedures to
accomplish the replacement required by this paragraph.
(ii) Visually inspect each flex frame and mount bolt torque
stripe (red or yellow) for movement. If there is any torque stripe
movement, before further flight, replace the main driveshaft. The
main drive shaft may be overhauled in accordance with FAA-approved
procedures to accomplish the replacement required by this paragraph.
(iii) Visually inspect each joint for fretting corrosion, which
may be indicated by red metallic particles. If there is any grease,
oil, or dirt covering a joint, clean the area and visually inspect
again. If there is any fretting corrosion, before further flight,
replace the main driveshaft. The main drive shaft may be overhauled
in accordance with FAA-approved procedures to accomplish the
replacement required by this paragraph.
(iv) Inspect the main driveshaft for mechanical damage,
corrosion, an edge dent, and nick as shown in Figure 3 to paragraph
(g)(3)(iv) of this AD. For the purposes of this inspection,
mechanical damage may be indicated by a crack, scratch, or wear; and
corrosion may be indicated by corrosion or pitting. If there is a
scratch, wear, corrosion, pitting, an edge dent, or a nick within
allowable limits, before further flight, repair the main driveshaft
in accordance with FAA-approved procedures. If there is a crack, or
a scratch, wear, corrosion, pitting, an edge dent, or a nick that
exceeds allowable limits,
[[Page 3181]]
before further flight, replace the main driveshaft. The main drive
shaft may be overhauled in accordance with FAA-approved procedures
to accomplish the replacement required by this paragraph.
[GRAPHIC] [TIFF OMITTED] TR21JA22.002
[[Page 3182]]
(4) Before installing the main driveshaft following paragraph
(g)(3) of this AD, and with the engine adapter installed in the end
of the engine output shaft, inspect the alignment of the main
driveshaft installation between the transmission input drive quill
coupling and the engine output shaft adapter by following ``6-24.
Alignment--Main Driveshaft,'' paragraphs c. through g. on pages 6-21
through 6-23, including ``Figure 6-7. Transmission Positioning for
Driveshaft Alignment'' on page 6-2 (Figure 6-7), and ``Figure 6-8.
Tool Application--Use of Alignment Tool Set (T47)'' on page 6-3
(Figure 6-8), of TM 55-1520-210-23-1 C 42. If there is misalignment,
before further flight, adjust the alignment by following ``6-24.
Alignment--Main Driveshaft,'' paragraphs h. through j. on page 6-23,
including Figure 6-7 and Figure 6-8, of TM 55-1520-210-23-1 C 42.
(5) Within 300 hours TIS after the effective date of this AD,
and thereafter within intervals not to exceed 300 hours TIS, with
the main driveshaft installed, accomplish the actions in paragraphs
(g)(3)(i) through (iv) of this AD.
(6) As an optional terminating action for the requirements of
this AD, you may install KAflex main driveshaft P/N SKCP3303-1.
(7) As an option to accomplishing the actions by following the
specified portions in TM 55-1520-210-23-1 C 42 in paragraphs (g)(3)
and (4) of this AD, you may accomplish the actions by following
those specified portions in Headquarters, Department of the Army,
Aviation Unit and Intermediate Maintenance Instructions Army Model
UH-1H/V/EH-1H/X Helicopters, Technical Manual TM 55-1520-210-23-1,
Change No. 47, dated September 20, 2005 (TM 55-1520-210-23-1 C 47),
and disregard exceptions to refer to Figure 1 and see Figure 2 to
the introductory text of paragraph (g)(3) of this AD, instead refer
to ``Figure 6-12.2. Main Driveshaft Installation & Removal Tool''
and see ``Figure 6-12.3. Work Aid Tool Installed on Main
Driveshaft,'' on page 6-27 of TM 55-1520-210-23-1 C 47 as instructed
in TM 55-1520-210-23-1 C 47.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, DSCO 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
certification office, send it to the attention of the person
identified in paragraph (i) of this AD. Information may be emailed
to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(i) Related Information
For more information about this AD, contact Ameet Shrotriya,
Aerospace Engineer, Delegation Oversight Section, DSCO Branch,
Compliance & Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222-5525; email
[email protected].
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) 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) Headquarters, Department of the Army, Aviation Unit and
Intermediate Maintenance Instructions Army Model UH-1H/V/EH-1H/X
Helicopters, Technical Manual TM 55-1520-210-23-1, Change No. 42,
dated April 14, 2003:
(A) ``Figure 4-9. Engine Air Inlet Filter Installation,'' page
4-16;
(B) Page 4-17;
(C) ``Figure 6-7. Transmission Positioning for Driveshaft
Alignment,'' page 6-2;
(D) ``Figure 6-8. Tool Application--Use of Alignment Tool Set
(T47),'' page 6-3; and
(E) Pages 6-21 through 6-24.
(ii) Headquarters, Department of the Army, Aviation Unit and
Intermediate Maintenance Instructions Army Model UH-1H/V/EH-1H/X
Helicopters, Technical Manual TM 55-1520-210-23-1, Change No. 47,
dated September 20, 2005:
(A) ``Figure 4-9. Engine Air Inlet Filter Installation,'' page
4-16;
(B) Page 4-17;
(C) ``Figure 6-7. Transmission Positioning for Driveshaft
Alignment,'' page 6-2;
(D) ``Figure 6-8. Tool Application--Use of Alignment Tool Set
(T47),'' page 6-3;
(E) Pages 6-21 through 6-24; and
(F) ``Figure 6-12.2. Main Driveshaft Installation & Removal
Tool'' and ``Figure 6-12.3. Work Aid Tool Installed on Main
Driveshaft,'' page 6-27.
(3) For service information identified in this AD, contact U.S.
Army Materiel Command Logistics Data Analysis Center (USAMC LDAC),
ATTN: Equipment Publication Control Officers (EPCOs), Building 3305,
Redeye Road, Redstone Arsenal, AL 35898-7466; telephone (256) 955-
7716 or 1-866-211-3367; email
[email protected]; or at https://enterprise.armyerp.army.mil.
(4) You may view this service information at 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.
Issued on December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-00991 Filed 1-20-22; 8:45 am]
BILLING CODE 4910-13-P
