Airworthiness Directives; Hamilton Sundstrand Corporation Propellers, 36145-36148 [2020-12821]
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Federal Register / Vol. 85, No. 115 / Monday, June 15, 2020 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Airplane Flight Manual Revisions
Within 30 days after the effective date of
this AD, revise your airplane flight manual
(AFM) by incorporating the revision
applicable to your airplane configuration as
listed in paragraphs (g)(1) through (3) of this
AD:
(1) Gulfstream IV Airplane Flight Manual,
Gulfstream Aerospace Document Number
GAC–AC–GIV–OPS–0001, Revision 52, dated
October 30, 2017;
(2) Gulfstream G300 Airplane Flight
Manual, Gulfstream Aerospace Document
Number GAC–AC–G300–OPS–0001, Revision
20, dated October 30, 2017; or
(3) Gulfstream G400 Airplane Flight
Manual, Gulfstream Aerospace Document
Number FAC–AC–G400–OPS–0001, Revision
20, dated October 30, 2017.
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(h) Replace the Nose Wheel Steering Servo
Valve Manifold
Within 36 months after the effective date
of this AD, replace the nose wheel steering
servo valve manifold with nose wheel
steering servo valve manifold part number
5100–11 or 5105–5 in accordance with the
Accomplishment Instructions of the
customer bulletin that applies to your
airplane configuration as listed in paragraphs
(h)(1) through (3) of this AD, except you are
not required to comply with step H:
(1) Gulfstream IV Customer Bulletin
Number 244, dated March 12, 2018;
(2) Gulfstream G300 Customer Bulletin
244, dated March 12, 2018; or
(3) Gulfstream G400 Customer Bulletin
244, dated March 12, 2018.
(i) Records Inspection and Report of Results
(1) Between 12 months and 24 months after
the replacement of the nose wheel steering
valve manifold assembly required in
paragraph (h) of this AD, inspect all aircraft
records for entries of an un-commanded nose
wheel steering turn.
(2) Within 10 days after the records
inspection required in paragraph (i)(1) of this
AD, report the results of the inspection,
regardless of whether the inspection found
any entries, to the FAA by either email: 9ASO&-ATLCOS-Reporting@faa.gov; or by
mail: Attn: Continued Operational Safety,
Atlanta ACO Branch, FAA, 1701 Columbia
Avenue, College Park, Georgia 30337. The
report must include as much of the
information listed in paragraphs (i)(2)(i)
through (vii) of this AD as is known about
the event:
(i) Date of records inspection;
(ii) Date and time of all un-commanded
occurrences (if any);
(iii) Airplane serial number;
(iv) Weather and runway conditions at the
time of each occurrence;
(v) Copy of the pilot’s report of the
occurrence (if available);
(vi) Maintenance entry of the root cause of
the un-commanded deflection (if available);
and
(vii) Any other information pertinent to the
occurrence.
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(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Atlanta ACO 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 (k)(1) of
this AD.
(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.
For more information about this AD,
contact Alex Armas, Aerospace Engineer,
Atlanta ACO Branch, FAA, 1701 Columbia
Avenue, College Park, Georgia 30337; phone:
(404) 474–5538; fax: (404) 474–5605; email:
alex.armas@faa.gov.
(l) 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) Gulfstream IV Customer Bulletin
Number 244, dated March 12, 2018.
(ii) Gulfstream G300 Customer Bulletin
Number 244, dated March 12, 2018.
(iii) Gulfstream G400 Customer Bulletin
Number 244, dated March 12, 2018.
(iv) Gulfstream IV Airplane Flight Manual,
Gulfstream Aerospace Document Number
GAC–AC–GIV–OPS–0001, Revision 52, dated
October 30, 2017.
(v) Gulfstream G300 Airplane Flight
Manual, Gulfstream Aerospace Document
Number GAC–AC–G300–OPS–0001, Revision
20, dated October 30, 2017.
(vi) Gulfstream G400 Airplane Flight
Manual, Gulfstream Aerospace Document
Number FAC–AC–G400–OPS–0001, Revision
20, dated October 30, 2017.
(3) For service information identified in
this AD, contact Gulfstream Aerospace
Corporation, P.O. Box 2206, Savannah,
Georgia 31402–2206; telephone: (800) 810–
4853; fax 912–965–3520; email: pubs@
gulfstream.com; internet: https://
www.gulfstream.com/customer-support.
(4) You may view this service information
at FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
(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: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
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Issued on June 2, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–12812 Filed 6–12–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–1008; Project
Identifier AD–2019–00110–P; Amendment
39–21142; AD 2020–12–07]
RIN 2120–AA64
(k) Related Information
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Airworthiness Directives; Hamilton
Sundstrand Corporation Propellers
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Hamilton Sundstrand Corporation
(Hamilton Sundstrand) 54H60 model
propellers. This AD was prompted by
the failure of a propeller blade that
resulted in the loss of the airplane. This
AD requires initial and repetitive eddy
current inspections (ECIs) of the affected
propeller blades and replacement of the
propeller blades that fail the inspection.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective July 20,
2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 20, 2020.
ADDRESSES: For service information
identified in this final rule, contact
Hamilton Sundstrand, 1 Hamilton Road,
Windsor Locks, CT 06096–1010, United
States; phone: (877) 808–7575; email:
CRC@collins.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 781–238–7759.
It is also available on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2019–1008.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
1008; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
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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:
Maureen Maisttison, Aerospace
Engineer, Boston ACO Branch, FAA,
1200 District Avenue, Burlington, MA
01803; phone: 781–238–7076; fax: 781–
238–7199; email: maureen.maisttison@
faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Hamilton Sundstrand
54H60 model propellers. The NPRM
published in the Federal Register on
January 28, 2020 (85 FR 4916). The
NPRM was prompted by a report of the
separation of a 54H60 model propeller
blade installed on a United States
Marine Corps Reserve (USMCR) KC–
130T airplane during a flight in July
2017.
The USMCR investigation of this
event revealed the Hamilton Sundstrand
54H60 model propeller blade separated
due to corrosion pitting and a resultant
intergranular radial crack that was not
corrected at the last propeller overhaul.
From this intergranular crack, a fatigue
crack initiated and grew under service
loading until the Hamilton Sundstrand
54H60 model propeller blade could no
longer sustain the applied loads and
ultimately the blade separated. The
separation of the blade resulted in the
loss of the airplane and 17 fatalities. The
investigation further revealed that
54H60 model propeller blades
manufactured before 1971 are
susceptible to cracks of the propeller
blade in the area of the internal taper
bore. The applicability of this AD is
therefore limited to those Hamilton
Sundstrand 54H60 model propellers
blades with a blade serial number below
813320, which are those propeller
blades manufactured before 1971.
The NPRM proposed to require initial
and repetitive ECIs of the affected
propeller blades and removal from
service of any blades that fail these
inspections. Propeller blade taper bore
cracks, if not detected, could result in
failure of the propeller blade, blade
separation, and loss of the airplane. The
FAA is issuing this AD to address the
unsafe condition on these products.
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Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received one
comment, from Lockheed Martin
Aeronautics Company (LMAC). The
following presents the FAA’s response.
Comment on Cause of Propeller Blade
Separation
LMAC commented that the
Discussion section of the NPRM
indicated that the propeller blade
separated from the KC–130T airplane as
the result of corrosion that was not
corrected at the last propeller overhaul.
LMAC noted that the investigation
completed by the U.S. Navy and the
U.S. Air Force concluded that the
separation was a result of a fatigue crack
which grew under service loading until
the blade could no longer sustain the
applied loads.
The FAA revised the Discussion
section of this final rule to state that the
investigation concluded that corrosion
pitting and a resultant intergranular
radial crack was not corrected at the last
propeller overhaul. From this
intergranular crack, a fatigue crack
initiated and grew under service loading
until the Hamilton Sundstrand 54H60
model propeller blade could no longer
sustain the applied loads and ultimately
the blade separated. No change to this
AD is required.
Comment on Difference in Compliance
Time
LMAC commented that the
compliance time in paragraphs (g)(1)
and (2) of the NPRM differs from the
time recommended by LMAC in its two
applicable Alert Service Bulletins
(ASBs): AV382–61–011, dated October
3, 2019, for all ‘‘382 models’’ (excluding
the 382J) and 88/SB–723, dated
November 6, 2019, for L–188 Electra
aircraft types. LMAC has recommended
that its customers comply with the
Hamilton Sundstrand ASB 54H60–61–
A154, dated August 26, 2019, within 90
days of receipt of the applicable aircrafttype LMAC ASB. LMAC stated that this
90-day compliance time was based on
an aircraft-level risk assessment that
considered the consequence of loss of
the propeller and the probability of
occurrence based on the reported cases
of intergranular cracking of the blade.
The FAA applied Advisory Circular
(AC) 39–8, ‘‘Continued Airworthiness
Assessments of Powerplant and
Auxiliary Power Unit Installations of
Transport Category Airplanes,’’ dated
September 8, 2003 (‘‘AC 39–8’’) to
identify the unsafe condition and to
assess the risk for propellers installed in
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transport aircraft. The FAA’s risk
assessment for the Hamilton Sundstrand
54H60 propeller affected by this AD did
not support the compliance interval
proposed by LMAC in its ASBs. The
FAA’s risk assessment did not justify
mandating that all blades be inspected
within 90 days, per the LMAC
recommendation. No change to this AD
is required.
Comment on Relationship Between
Unsafe Condition, Overhaul Period,
and Blade Cracking
LMAC commented that the severity of
this ‘‘hazard/unsafe condition’’ is not
influenced by the overhaul period and
there is no known correlation between
time since overhaul and probability of
intergranular cracking.
The FAA agrees that the severity of
this unsafe condition is not influenced
by the overhaul period and there is no
known correlation between time since
overhaul and probability of
intergranular cracking. There is little
established knowledge of this type of
intergranular crack initiation and
growth in this aluminum alloy, although
an investigation has been underway for
2 years. However, the FAA has
determined that since corrosion occurs
regardless of whether the propeller is in
service and corrosion has been
discovered in blades exhibiting
intergranular cracks, the appropriate
compliance time uses calendar time
after the effective date of this AD, based
on the time of the last overhaul.
This AD employs risk-based
inspections by placing priority on
inspecting blades that have higher
calendar time since their last overhaul
because these blades have a higher
probability of corrosion. In most cases,
corrosion has been found to exist in
conjunction with intergranular cracking.
Moreover, this AD imposes a mandatory
reporting requirement for cracked
blades and the FAA expects that such
blades will be subject to additional
metallurgical examinations intended to
identify factors influencing
intergranular cracking. The FAA may
consider further rulemaking action on
this unsafe condition, depending on the
results of these examinations. No
change to this AD is required.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule as proposed except for minor
editorial changes. These minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
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• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Hamilton
Sundstrand Corporation ASB 54H60–
61–A154, dated August 26, 2019. The
ASB describes procedures for
performing an ECI of the propeller blade
taper bore. 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.
Interim Action
The FAA considers this AD interim
action. The root cause of the 54H60
model propeller blade separation is still
under investigation. The FAA may
consider further rulemaking action.
Costs of Compliance
The FAA estimates that this AD
affects 212 propellers installed on 53
aircraft of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
ESTIMATED COSTS
Action
Labor cost
ECI of propeller .......................
8 work-hours × $85 per hour = $680 .....................................
The FAA estimates the following
costs to do any necessary replacements
that would be required based on the
Parts cost
results of the inspection. The FAA has
no way of determining the number of
Cost per
product
$700
Cost on U.S.
operators
$1,380
$292,560
aircraft that might need these
replacements:
ON-CONDITION COSTS
Action
Labor cost
Replace blade ..................................
1 work-hour × $85 per hour = $85 ............................................................
Paperwork Reduction Act
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A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to a penalty for failure to comply with
a collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a currently valid
OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public
reporting for this collection of
information is estimated to be
approximately 1 hour per response,
including the time for reviewing
instructions, searching existing data
sources, gathering and maintaining the
data needed, 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:
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Parts cost
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: ‘‘General requirements.’’ Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
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Cost per
product
$63,500
$63,585
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.
Adoption of 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
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 (AD):
■
2020–12–07 Hamilton Sundstrand
Corporation: Amendment 39–21142;
Docket No. FAA–2019–1008; Project
Identifier AD–2019–00110–P.
(a) Effective Date
This AD is effective July 20, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Hamilton
Sundstrand Corporation (Hamilton
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Sundstrand) model 54H60 propellers with a
blade having a serial number (S/N) below
S/N 813320.
(d) Subject
Joint Aircraft System Component (JASC)
Code 6111, Propeller Blade Section.
(e) Unsafe Condition
This AD was prompted by the separation
of a propeller blade that resulted in the loss
of an airplane and 17 fatalities. The FAA is
issuing this AD to detect cracking in the
propeller blade taper bore. The unsafe
condition, if not addressed, could result in
failure of the propeller blade, blade
separation, and loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For affected propellers identified in
Planning Information, paragraph 1.E.(1), of
Hamilton Sundstrand Corporation Alert
Service Bulletin (ASB) 54H60–61–A154,
dated August 26, 2019 (‘‘the ASB’’), perform
an eddy current inspection (ECI) of all blades
installed on the propeller within one year or
500 flight hours after the effective date of this
AD, whichever occurs first.
(2) For affected propellers identified in
Planning Information, paragraph 1.E.(2), of
the ASB, perform an ECI of all blades
installed on the propeller within two years or
1,000 flight hours after the effective date of
this AD, whichever occurs first.
(3) Perform the ECI of the affected
propeller blades using the Accomplishment
Instructions, paragraph 3.C. of the ASB.
(4) If any propeller blade fails any
inspection required by this AD, based on the
criteria in paragraph 3.C. of the ASB, remove
the blade from service and replace with a
blade eligible for installation prior to the next
flight.
(5) For all affected propellers, repeat the
inspection required by paragraphs (g)(1)
through (4) of this AD at intervals not
exceeding 3 years or 1,500 flight hours,
whichever comes first, after the previous
inspection.
(6) Report the results of the ECI required
by paragraphs (g)(1) through (5) of this AD in
accordance with the Accomplishment
Instructions, paragraph 3.C.(6) of the ASB.
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(h) Installation Prohibition
After the effective date of this AD, do not
install any Hamilton Sundstrand propeller
blades having an S/N below 813320 on any
propeller, unless the blade has first passed
the inspection required by this AD. After the
effective date of this AD, do not install any
propeller assemblies with affected propeller
blades onto any aircraft unless the affected
propeller blades have passed the inspection
required by paragraph (g) of this AD.
(i) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
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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 be approximately 1 hour per
response, including the time for reviewing
instructions, searching existing data sources,
gathering and maintaining the data needed,
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.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Boston ACO 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 (k) of this
AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(k) Related Information
For more information about this AD,
contact Maureen Maisttison, Aerospace
Engineer, Boston ACO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: 781–238–7076; fax: 781–238–7199;
email: maureen.maisttison@faa.gov.
(l) 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) Hamilton Sundstrand Corporation
(Hamilton Sundstrand) Alert Service Bulletin
54H60–61–A154, dated August 26, 2019.
(ii) [Reserved]
(3) For Hamilton Sundstrand service
information identified in this AD, contact
Hamilton Sundstrand, 1 Hamilton Road,
Windsor Locks, CT 06096–1010, United
States; phone: (877) 808–7575; email: CRC@
collins.com.
(4) 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 781–238–7759.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
PO 00000
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Administration (NARA). For information on
the availability of this material at NARA,
email: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on June 3, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–12821 Filed 6–12–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF JUSTICE
Drug Enforcement Administration
21 CFR Part 1308
[Docket No. DEA–601]
Schedules of Controlled Substances:
Exempt Anabolic Steroid Products
Drug Enforcement
Administration, Department of Justice.
ACTION: Order with opportunity for
comment.
AGENCY:
The Drug Enforcement
Administration is designating two
pharmaceutical preparations containing
esterified estrogens and
methyltestosterone as exempt anabolic
steroid products under the Controlled
Substances Act.
DATES: This order is effective June 15,
2020. Written comments must be
postmarked, and electronic comments
must be sent, on or before August 14,
2020.
ADDRESSES: To ensure proper handling
of comments, please reference ‘‘Docket
No. DEA–601’’ on all electronic and
written correspondence, including any
attachments.
• Electronic comments: The Drug
Enforcement Administration (DEA)
encourages that all comments be
submitted electronically through the
Federal eRulemaking Portal which
provides the ability to type short
comments directly into the comment
field on the web page or attach a file for
lengthier comments. Please go to https://
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online instructions at that site for
submitting comments. Upon completion
of your submission, you will receive a
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your comment has been successfully
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• Paper comments: Paper comments
that duplicate electronic submissions
SUMMARY:
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[Federal Register Volume 85, Number 115 (Monday, June 15, 2020)]
[Rules and Regulations]
[Pages 36145-36148]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-12821]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-1008; Project Identifier AD-2019-00110-P;
Amendment 39-21142; AD 2020-12-07]
RIN 2120-AA64
Airworthiness Directives; Hamilton Sundstrand Corporation
Propellers
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Hamilton Sundstrand Corporation (Hamilton Sundstrand) 54H60
model propellers. This AD was prompted by the failure of a propeller
blade that resulted in the loss of the airplane. This AD requires
initial and repetitive eddy current inspections (ECIs) of the affected
propeller blades and replacement of the propeller blades that fail the
inspection. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective July 20, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 20,
2020.
ADDRESSES: For service information identified in this final rule,
contact Hamilton Sundstrand, 1 Hamilton Road, Windsor Locks, CT 06096-
1010, United States; phone: (877) 808-7575; email: [email protected]. 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 781-238-7759. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
1008.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
1008; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday
[[Page 36146]]
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: Maureen Maisttison, Aerospace
Engineer, Boston ACO Branch, FAA, 1200 District Avenue, Burlington, MA
01803; phone: 781-238-7076; fax: 781-238-7199; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Hamilton
Sundstrand 54H60 model propellers. The NPRM published in the Federal
Register on January 28, 2020 (85 FR 4916). The NPRM was prompted by a
report of the separation of a 54H60 model propeller blade installed on
a United States Marine Corps Reserve (USMCR) KC-130T airplane during a
flight in July 2017.
The USMCR investigation of this event revealed the Hamilton
Sundstrand 54H60 model propeller blade separated due to corrosion
pitting and a resultant intergranular radial crack that was not
corrected at the last propeller overhaul. From this intergranular
crack, a fatigue crack initiated and grew under service loading until
the Hamilton Sundstrand 54H60 model propeller blade could no longer
sustain the applied loads and ultimately the blade separated. The
separation of the blade resulted in the loss of the airplane and 17
fatalities. The investigation further revealed that 54H60 model
propeller blades manufactured before 1971 are susceptible to cracks of
the propeller blade in the area of the internal taper bore. The
applicability of this AD is therefore limited to those Hamilton
Sundstrand 54H60 model propellers blades with a blade serial number
below 813320, which are those propeller blades manufactured before
1971.
The NPRM proposed to require initial and repetitive ECIs of the
affected propeller blades and removal from service of any blades that
fail these inspections. Propeller blade taper bore cracks, if not
detected, could result in failure of the propeller blade, blade
separation, and loss of the airplane. The FAA is issuing this AD to
address the unsafe condition on these products.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received one comment, from Lockheed
Martin Aeronautics Company (LMAC). The following presents the FAA's
response.
Comment on Cause of Propeller Blade Separation
LMAC commented that the Discussion section of the NPRM indicated
that the propeller blade separated from the KC-130T airplane as the
result of corrosion that was not corrected at the last propeller
overhaul. LMAC noted that the investigation completed by the U.S. Navy
and the U.S. Air Force concluded that the separation was a result of a
fatigue crack which grew under service loading until the blade could no
longer sustain the applied loads.
The FAA revised the Discussion section of this final rule to state
that the investigation concluded that corrosion pitting and a resultant
intergranular radial crack was not corrected at the last propeller
overhaul. From this intergranular crack, a fatigue crack initiated and
grew under service loading until the Hamilton Sundstrand 54H60 model
propeller blade could no longer sustain the applied loads and
ultimately the blade separated. No change to this AD is required.
Comment on Difference in Compliance Time
LMAC commented that the compliance time in paragraphs (g)(1) and
(2) of the NPRM differs from the time recommended by LMAC in its two
applicable Alert Service Bulletins (ASBs): AV382-61-011, dated October
3, 2019, for all ``382 models'' (excluding the 382J) and 88/SB-723,
dated November 6, 2019, for L-188 Electra aircraft types. LMAC has
recommended that its customers comply with the Hamilton Sundstrand ASB
54H60-61-A154, dated August 26, 2019, within 90 days of receipt of the
applicable aircraft-type LMAC ASB. LMAC stated that this 90-day
compliance time was based on an aircraft-level risk assessment that
considered the consequence of loss of the propeller and the probability
of occurrence based on the reported cases of intergranular cracking of
the blade.
The FAA applied Advisory Circular (AC) 39-8, ``Continued
Airworthiness Assessments of Powerplant and Auxiliary Power Unit
Installations of Transport Category Airplanes,'' dated September 8,
2003 (``AC 39-8'') to identify the unsafe condition and to assess the
risk for propellers installed in transport aircraft. The FAA's risk
assessment for the Hamilton Sundstrand 54H60 propeller affected by this
AD did not support the compliance interval proposed by LMAC in its
ASBs. The FAA's risk assessment did not justify mandating that all
blades be inspected within 90 days, per the LMAC recommendation. No
change to this AD is required.
Comment on Relationship Between Unsafe Condition, Overhaul Period, and
Blade Cracking
LMAC commented that the severity of this ``hazard/unsafe
condition'' is not influenced by the overhaul period and there is no
known correlation between time since overhaul and probability of
intergranular cracking.
The FAA agrees that the severity of this unsafe condition is not
influenced by the overhaul period and there is no known correlation
between time since overhaul and probability of intergranular cracking.
There is little established knowledge of this type of intergranular
crack initiation and growth in this aluminum alloy, although an
investigation has been underway for 2 years. However, the FAA has
determined that since corrosion occurs regardless of whether the
propeller is in service and corrosion has been discovered in blades
exhibiting intergranular cracks, the appropriate compliance time uses
calendar time after the effective date of this AD, based on the time of
the last overhaul.
This AD employs risk-based inspections by placing priority on
inspecting blades that have higher calendar time since their last
overhaul because these blades have a higher probability of corrosion.
In most cases, corrosion has been found to exist in conjunction with
intergranular cracking. Moreover, this AD imposes a mandatory reporting
requirement for cracked blades and the FAA expects that such blades
will be subject to additional metallurgical examinations intended to
identify factors influencing intergranular cracking. The FAA may
consider further rulemaking action on this unsafe condition, depending
on the results of these examinations. No change to this AD is required.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule as proposed except for minor editorial
changes. These minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
[[Page 36147]]
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Hamilton Sundstrand Corporation ASB 54H60-61-A154,
dated August 26, 2019. The ASB describes procedures for performing an
ECI of the propeller blade taper bore. 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.
Interim Action
The FAA considers this AD interim action. The root cause of the
54H60 model propeller blade separation is still under investigation.
The FAA may consider further rulemaking action.
Costs of Compliance
The FAA estimates that this AD affects 212 propellers installed on
53 aircraft of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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ECI of propeller................... 8 work-hours x $85 per hour $700 $1,380 $292,560
= $680.
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The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
inspection. The FAA has no way of determining the number of aircraft
that might need these replacements:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Replace blade.............................. 1 work-hour x $85 per hour = $85... $63,500 $63,585
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Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to be
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory. Send comments regarding this burden estimate or any other
aspect of this collection of information, including suggestions for
reducing this burden to: Information Collection Clearance Officer,
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX
76177-1524.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2020-12-07 Hamilton Sundstrand Corporation: Amendment 39-21142;
Docket No. FAA-2019-1008; Project Identifier AD-2019-00110-P.
(a) Effective Date
This AD is effective July 20, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Hamilton Sundstrand Corporation (Hamilton
[[Page 36148]]
Sundstrand) model 54H60 propellers with a blade having a serial
number (S/N) below S/N 813320.
(d) Subject
Joint Aircraft System Component (JASC) Code 6111, Propeller
Blade Section.
(e) Unsafe Condition
This AD was prompted by the separation of a propeller blade that
resulted in the loss of an airplane and 17 fatalities. The FAA is
issuing this AD to detect cracking in the propeller blade taper
bore. The unsafe condition, if not addressed, could result in
failure of the propeller blade, blade separation, and loss of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For affected propellers identified in Planning Information,
paragraph 1.E.(1), of Hamilton Sundstrand Corporation Alert Service
Bulletin (ASB) 54H60-61-A154, dated August 26, 2019 (``the ASB''),
perform an eddy current inspection (ECI) of all blades installed on
the propeller within one year or 500 flight hours after the
effective date of this AD, whichever occurs first.
(2) For affected propellers identified in Planning Information,
paragraph 1.E.(2), of the ASB, perform an ECI of all blades
installed on the propeller within two years or 1,000 flight hours
after the effective date of this AD, whichever occurs first.
(3) Perform the ECI of the affected propeller blades using the
Accomplishment Instructions, paragraph 3.C. of the ASB.
(4) If any propeller blade fails any inspection required by this
AD, based on the criteria in paragraph 3.C. of the ASB, remove the
blade from service and replace with a blade eligible for
installation prior to the next flight.
(5) For all affected propellers, repeat the inspection required
by paragraphs (g)(1) through (4) of this AD at intervals not
exceeding 3 years or 1,500 flight hours, whichever comes first,
after the previous inspection.
(6) Report the results of the ECI required by paragraphs (g)(1)
through (5) of this AD in accordance with the Accomplishment
Instructions, paragraph 3.C.(6) of the ASB.
(h) Installation Prohibition
After the effective date of this AD, do not install any Hamilton
Sundstrand propeller blades having an S/N below 813320 on any
propeller, unless the blade has first passed the inspection required
by this AD. After the effective date of this AD, do not install any
propeller assemblies with affected propeller blades onto any
aircraft unless the affected propeller blades have passed the
inspection required by paragraph (g) of this AD.
(i) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a currently valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 1 hour per response, including the
time for reviewing instructions, searching existing data sources,
gathering and maintaining the data needed, 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.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Boston ACO 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 (k) of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(k) Related Information
For more information about this AD, contact Maureen Maisttison,
Aerospace Engineer, Boston ACO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781-238-7076; fax: 781-238-7199; email:
[email protected].
(l) 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) Hamilton Sundstrand Corporation (Hamilton Sundstrand) Alert
Service Bulletin 54H60-61-A154, dated August 26, 2019.
(ii) [Reserved]
(3) For Hamilton Sundstrand service information identified in
this AD, contact Hamilton Sundstrand, 1 Hamilton Road, Windsor
Locks, CT 06096-1010, United States; phone: (877) 808-7575; email:
[email protected].
(4) 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 781-238-7759.
(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 June 3, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-12821 Filed 6-12-20; 8:45 am]
BILLING CODE 4910-13-P
