Special Conditions: CFM International, LEAP-1A and -1C Engine Models; Incorporation of Woven Composite Fan Blades, 32440-32441 [2015-14084]
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Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations
Accordingly, 7 CFR part 633 is
amended as follows:
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*
*
*
Person means one or more
individuals, partnerships, associations,
corporations, estates or trusts, or other
business enterprises or other legal
entities and, whenever applicable, an
Indian tribe, a State, a political
subdivision of a State, or any agency
thereof.
*
*
*
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*
Privately-owned means owned or
operated by a person other than a State,
a political subdivision of a State, or any
agency thereof.
*
*
*
*
*
■ 3. Section 633.4 is amended by
revising paragraph (d)(2) to read as
follows:
These special conditions are
issued for the CFM International (CFM),
LEAP–1A and –1C engine models.
These engine models will have a novel
or unusual design feature associated
with the engine fan blades—new woven
composite fan blades. The applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
for this design feature. These special
conditions contain the additional safety
standards that the Administrator
considers necessary to establish a level
of safety equivalent to that established
by the existing airworthiness standards.
DATES: Effective July 9, 2015.
FOR FURTHER INFORMATION CONTACT: For
technical questions concerning this
action, contact Alan Strom, ANE–111,
Engine and Propeller Directorate,
Aircraft Certification Service, 12 New
England Executive Park, Burlington,
Massachusetts 01803; telephone (781)
238–7143; facsimile (781) 238–7199;
email alan.strom@faa.gov.
For legal questions concerning this
action, contact Vincent Bennett, ANE–7,
Engine and Propeller Directorate,
Aircraft Certification Service, 12 New
England Executive Park, Burlington,
Massachusetts 01803; telephone (781)
238–7044; facsimile (781) 238–7055;
email vincent.bennett@faa.gov.
SUPPLEMENTARY INFORMATION:
§ 633.4
Background
SUMMARY:
PART 633—WATER BANK PROGRAM
1. The authority citation for part 633
continues to read as follows:
■
Authority: 16 U.S.C. 1301–1311.
2. Section 633.2 is amended by
revising the definition for ‘‘Person’’ and
adding a definition in alphabetical order
for ‘‘Privately-owned’’ to read as
follows:
■
§ 633.2
Definitions.
*
Program requirements.
*
*
*
*
*
(d) * * *
(2) Lands owned by an agency of the
United States other than land held in
trust for Indian Tribes;
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*
*
*
*
Signed this 29 day of May, 2015 in
Washington, DC
Jason A. Weller,
Chief, Natural Resources Conservation
Service.
[FR Doc. 2015–13992 Filed 6–8–15; 8:45 am]
BILLING CODE 3410–16–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 33
tkelley on DSK3SPTVN1PROD with RULES
[Docket No. FAA–2014–0637; Special
Conditions No. 33–015–SC]
Special Conditions: CFM International,
LEAP–1A and –1C Engine Models;
Incorporation of Woven Composite
Fan Blades
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
VerDate Sep<11>2014
15:56 Jun 08, 2015
Jkt 235001
On June 27, 2012, CFM International
(CFM) applied for a type certificate for
their new LEAP–1A and –1C engine
models. The LEAP engine models are
high-bypass-ratio engines that
incorporate a novel and unusual design
feature—new woven composite fan
blades. The woven composite fan blades
will have significant differences in
material property characteristics when
compared to conventionally designed
fan blades using non-composite metallic
materials.
Special conditions are required to
ensure that the LEAP–1A and –1C
woven composite design fan blades
account for the differences in material
properties and failure modes relative to
conventional single-load path metallic
blades. In addition, different
containment requirements may be
applied provided CFM shows that the
blade design below the inner annulus
flow path line provides multiple load
paths and crack arresting features that
prevent delamination or crack
propagation to blade failure during the
life of the blade.
These special conditions are
necessary because the applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
for the new woven composite design fan
blades.
Type Certification Basis
Under the provisions of Title 14, Code
of Federal Regulations (14 CFR) 21.17,
CFM must show that the LEAP–1A and
–1C engine models meet the applicable
provisions of the applicable regulations
in effect on the date of application,
except as detailed in paragraphs
21.101(b) and (c). The FAA has
determined the following certification
basis for the LEAP–1A and –1C engine
models:
1. 14 CFR part 33, ‘‘Airworthiness
Standards: Aircraft Engines,’’ dated
February 1, 1965, with Amendments
33–1 through 33–32, dated September
20, 2012.
If the FAA finds that the regulations
in effect on the date of the application
for the change do not provide adequate
or appropriate safety standards for the
LEAP–1A and –1C engine models
because of a novel or unusual design
feature, special conditions are
prescribed under the provisions of
§ 21.16.
Special conditions are initially
applicable to the engine model for
which they are issued. Should the type
certificate for that engine model be
amended later to include any other
engine model that incorporates the same
novel or unusual design feature, the
special conditions would also apply to
the other engine model under § 21.101.
In addition to complying with the
applicable product airworthiness
regulations and special conditions, the
LEAP–1A and –1C engine models must
comply with the fuel venting and
exhaust emission requirements of 14
CFR part 34.
The FAA issues special conditions, as
defined in 14 CFR 11.19, in accordance
with § 11.38, and they become part of
the type-certification basis under
§ 21.17(a)(2).
Novel or Unusual Design Features
The LEAP–1A and –1C engine models
will incorporate the following novel or
unusual design feature:
The LEAP–1A and –1C engine models
will incorporate woven composite fan
blades. The woven composite fan blades
will have significant differences in
material property characteristics when
compared to conventionally designed
fan blades using non-composite metallic
materials. Composite material design
provides the capability to incorporate
multiple load paths and crack arresting
features that prevent delamination or
crack propagation to blade failure
during the life of the blade.
E:\FR\FM\09JNR1.SGM
09JNR1
Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations
The woven composite fan blades are
a novel and unusual design feature that
requires additional airworthiness
standards for type certification of the
LEAP–1A and –1C engine models.
Discussion of Comments
A notice of proposed special
conditions, No. 33–14–02–SC, for the
CFM LEAP–1A and—1C engine models
was published in the Federal Register
on Friday, November 14, 2014 (79 FR
68137). No comments were received and
the special conditions are adopted as
proposed.
Applicability
As discussed above, these special
conditions are applicable to the LEAP
–1A and –1C engine models. Should
CFM apply at a later date for a change
to the type certificate to include another
model on the same type certificate
incorporating the same novel or unusual
design feature, the special conditions
would apply to that model as well.
Conclusion
This action affects only certain novel
or unusual design features on LEAP–1A
and –1C engine models. It is not a rule
of general applicability and applies only
to CFM, who requested FAA approval of
this engine feature.
List of Subjects in 14 CFR Part 33
Aircraft, Engines, Aviation Safety,
Reporting and recordkeeping
requirements.
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
tkelley on DSK3SPTVN1PROD with RULES
The Special Conditions
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the following special
conditions are issued as part of the type
certification basis for CFM LEAP–1A
and –1C engine models.
1. Part 33, Requirements
In addition to the airworthiness
standards in 14 CFR part 33, effective
February 1, 1965, with Amendments
33–1 through 33–32 applicable to the
LEAP–1A and –1C engine models, CFM
will:
(a) Conduct an engine fan blade
containment test with the fan blade
failing at the inner annulus flow path
line instead of at the outermost
retention groove.
(b) Substantiate by test and analysis,
or other methods acceptable to the FAA,
that a fan disk and fan blade retention
system with minimum material
properties can withstand, without
VerDate Sep<11>2014
15:56 Jun 08, 2015
Jkt 235001
failure, a centrifugal load equal to two
times the maximum load the retention
system could experience within
approved engine operating limitations.
The fan blade retention system includes
the portion of the fan blade from the
inner annulus flow path line inward to
the blade dovetail, the blade retention
components, and the fan disk and fan
blade attachment features.
(c) Using a procedure approved by the
FAA, establish an operating limitation
that specifies the maximum allowable
number of start-stop stress cycles for the
fan blade retention system. The life
evaluation must include the combined
effects of high-cycle and low-cycle
fatigue. If the operating limitation is less
than 100,000 cycles, that limitation
must be specified in Chapter 5 of the
Engine Manual Airworthiness
Limitations Section. The procedure
used to establish the maximum
allowable number of start-stop stress
cycles for the fan blade retention system
will incorporate the integrity
requirements in paragraphs (c)(1), (c)(2),
and (c)(3) of these special conditions for
the fan blade retention system.
(1) An engineering plan, which
establishes and maintains that the
combinations of loads, material
properties, environmental influences,
and operating conditions, including the
effects of parts influencing these
parameters, are well known or
predictable through validated analysis,
test, or service experience.
(2) A manufacturing plan that
identifies the specific manufacturing
constraints necessary to consistently
produce the fan blade retention system
with the attributes required by the
engineering plan.
(3) A service management plan that
defines in-service processes for
maintenance and repair of the fan blade
retention system, which will maintain
attributes consistent with those required
by the engineering plan.
(d) Substantiate by test and analysis,
or other methods acceptable to the FAA,
that the blade design below the inner
annulus flow path line provides
multiple load paths and crack arresting
features that prevent delamination or
crack propagation to blade failure
during the life of the blade.
(e) Substantiate that during the
service life of the engine, the total
probability of an individual blade
retention system failure resulting from
all possible causes, as defined in
§ 33.75, will be extremely improbable
with a cumulative calculated probability
of failure of less than 10¥9 per engine
flight hour.
(f) Substantiate by test or analysis that
not only will the engine continue to
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
32441
meet the requirements of § 33.75
following a lightning strike on the
composite fan blade structure, but that
the lightning strike will not cause
damage to the fan blades that would
prevent continued safe operation of the
affected engine.
(g) Account for the effects of inservice deterioration, manufacturing
variations, minimum material
properties, and environmental effects
during the tests and analyses required
by paragraphs (a), (b), (c), (d), (e), and
(f) of these special conditions.
(h) Propose fleet leader monitoring
and field sampling programs that will
monitor the effects of engine fan blade
usage and fan blade retention system
integrity.
(i) Mark each fan blade legibly and
permanently with a part number and a
serial number.
Issued in Burlington, Massachusetts, on
June 1, 2015.
Ann C. Mollica,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2015–14084 Filed 6–8–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0227; Directorate
Identifier 2013–NM–211–AD; Amendment
39–18165; AD 2015–11–02]
RIN 2120–AA64
Airworthiness Directives; Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 95–26–11
for all Lockheed Martin Corporation/
Lockheed Martin Aeronautics Company
Model L–1011 series airplanes. AD 95–
26–11 required repetitive inspections to
detect cracking of the fittings that attach
the aft pressure bulkhead to the fuselage
stringers, repetitive inspections to detect
cracking of the fittings and of the splice
tab of the aft pressure bulkhead, and
corrective actions if necessary. This new
AD requires repetitive inspections to
detect cracking of the fittings that attach
the aft pressure bulkhead to the fuselage
stringers, repetitive inspections to detect
cracking of the fittings and of the splice
tab of the aft pressure bulkhead,
repetitive inspections for cracking of
SUMMARY:
E:\FR\FM\09JNR1.SGM
09JNR1
]]>Agencies
[Federal Register Volume 80, Number 110 (Tuesday, June 9, 2015)]
[Rules and Regulations]
[Pages 32440-32441]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-14084]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 33
[Docket No. FAA-2014-0637; Special Conditions No. 33-015-SC]
Special Conditions: CFM International, LEAP-1A and -1C Engine
Models; Incorporation of Woven Composite Fan Blades
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the CFM International
(CFM), LEAP-1A and -1C engine models. These engine models will have a
novel or unusual design feature associated with the engine fan blades--
new woven composite fan blades. The applicable airworthiness
regulations do not contain adequate or appropriate safety standards for
this design feature. These special conditions contain the additional
safety standards that the Administrator considers necessary to
establish a level of safety equivalent to that established by the
existing airworthiness standards.
DATES: Effective July 9, 2015.
FOR FURTHER INFORMATION CONTACT: For technical questions concerning
this action, contact Alan Strom, ANE-111, Engine and Propeller
Directorate, Aircraft Certification Service, 12 New England Executive
Park, Burlington, Massachusetts 01803; telephone (781) 238-7143;
facsimile (781) 238-7199; email alan.strom@faa.gov.
For legal questions concerning this action, contact Vincent
Bennett, ANE-7, Engine and Propeller Directorate, Aircraft
Certification Service, 12 New England Executive Park, Burlington,
Massachusetts 01803; telephone (781) 238-7044; facsimile (781) 238-
7055; email vincent.bennett@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
On June 27, 2012, CFM International (CFM) applied for a type
certificate for their new LEAP-1A and -1C engine models. The LEAP
engine models are high-bypass-ratio engines that incorporate a novel
and unusual design feature--new woven composite fan blades. The woven
composite fan blades will have significant differences in material
property characteristics when compared to conventionally designed fan
blades using non-composite metallic materials.
Special conditions are required to ensure that the LEAP-1A and -1C
woven composite design fan blades account for the differences in
material properties and failure modes relative to conventional single-
load path metallic blades. In addition, different containment
requirements may be applied provided CFM shows that the blade design
below the inner annulus flow path line provides multiple load paths and
crack arresting features that prevent delamination or crack propagation
to blade failure during the life of the blade.
These special conditions are necessary because the applicable
airworthiness regulations do not contain adequate or appropriate safety
standards for the new woven composite design fan blades.
Type Certification Basis
Under the provisions of Title 14, Code of Federal Regulations (14
CFR) 21.17, CFM must show that the LEAP-1A and -1C engine models meet
the applicable provisions of the applicable regulations in effect on
the date of application, except as detailed in paragraphs 21.101(b) and
(c). The FAA has determined the following certification basis for the
LEAP-1A and -1C engine models:
1. 14 CFR part 33, ``Airworthiness Standards: Aircraft Engines,''
dated February 1, 1965, with Amendments 33-1 through 33-32, dated
September 20, 2012.
If the FAA finds that the regulations in effect on the date of the
application for the change do not provide adequate or appropriate
safety standards for the LEAP-1A and -1C engine models because of a
novel or unusual design feature, special conditions are prescribed
under the provisions of Sec. 21.16.
Special conditions are initially applicable to the engine model for
which they are issued. Should the type certificate for that engine
model be amended later to include any other engine model that
incorporates the same novel or unusual design feature, the special
conditions would also apply to the other engine model under Sec.
21.101.
In addition to complying with the applicable product airworthiness
regulations and special conditions, the LEAP-1A and -1C engine models
must comply with the fuel venting and exhaust emission requirements of
14 CFR part 34.
The FAA issues special conditions, as defined in 14 CFR 11.19, in
accordance with Sec. 11.38, and they become part of the type-
certification basis under Sec. 21.17(a)(2).
Novel or Unusual Design Features
The LEAP-1A and -1C engine models will incorporate the following
novel or unusual design feature:
The LEAP-1A and -1C engine models will incorporate woven composite
fan blades. The woven composite fan blades will have significant
differences in material property characteristics when compared to
conventionally designed fan blades using non-composite metallic
materials. Composite material design provides the capability to
incorporate multiple load paths and crack arresting features that
prevent delamination or crack propagation to blade failure during the
life of the blade.
[[Page 32441]]
The woven composite fan blades are a novel and unusual design
feature that requires additional airworthiness standards for type
certification of the LEAP-1A and -1C engine models.
Discussion of Comments
A notice of proposed special conditions, No. 33-14-02-SC, for the
CFM LEAP-1A and--1C engine models was published in the Federal Register
on Friday, November 14, 2014 (79 FR 68137). No comments were received
and the special conditions are adopted as proposed.
Applicability
As discussed above, these special conditions are applicable to the
LEAP -1A and -1C engine models. Should CFM apply at a later date for a
change to the type certificate to include another model on the same
type certificate incorporating the same novel or unusual design
feature, the special conditions would apply to that model as well.
Conclusion
This action affects only certain novel or unusual design features
on LEAP-1A and -1C engine models. It is not a rule of general
applicability and applies only to CFM, who requested FAA approval of
this engine feature.
List of Subjects in 14 CFR Part 33
Aircraft, Engines, Aviation Safety, Reporting and recordkeeping
requirements.
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
The Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued as part of
the type certification basis for CFM LEAP-1A and -1C engine models.
1. Part 33, Requirements
In addition to the airworthiness standards in 14 CFR part 33,
effective February 1, 1965, with Amendments 33-1 through 33-32
applicable to the LEAP-1A and -1C engine models, CFM will:
(a) Conduct an engine fan blade containment test with the fan blade
failing at the inner annulus flow path line instead of at the outermost
retention groove.
(b) Substantiate by test and analysis, or other methods acceptable
to the FAA, that a fan disk and fan blade retention system with minimum
material properties can withstand, without failure, a centrifugal load
equal to two times the maximum load the retention system could
experience within approved engine operating limitations. The fan blade
retention system includes the portion of the fan blade from the inner
annulus flow path line inward to the blade dovetail, the blade
retention components, and the fan disk and fan blade attachment
features.
(c) Using a procedure approved by the FAA, establish an operating
limitation that specifies the maximum allowable number of start-stop
stress cycles for the fan blade retention system. The life evaluation
must include the combined effects of high-cycle and low-cycle fatigue.
If the operating limitation is less than 100,000 cycles, that
limitation must be specified in Chapter 5 of the Engine Manual
Airworthiness Limitations Section. The procedure used to establish the
maximum allowable number of start-stop stress cycles for the fan blade
retention system will incorporate the integrity requirements in
paragraphs (c)(1), (c)(2), and (c)(3) of these special conditions for
the fan blade retention system.
(1) An engineering plan, which establishes and maintains that the
combinations of loads, material properties, environmental influences,
and operating conditions, including the effects of parts influencing
these parameters, are well known or predictable through validated
analysis, test, or service experience.
(2) A manufacturing plan that identifies the specific manufacturing
constraints necessary to consistently produce the fan blade retention
system with the attributes required by the engineering plan.
(3) A service management plan that defines in-service processes for
maintenance and repair of the fan blade retention system, which will
maintain attributes consistent with those required by the engineering
plan.
(d) Substantiate by test and analysis, or other methods acceptable
to the FAA, that the blade design below the inner annulus flow path
line provides multiple load paths and crack arresting features that
prevent delamination or crack propagation to blade failure during the
life of the blade.
(e) Substantiate that during the service life of the engine, the
total probability of an individual blade retention system failure
resulting from all possible causes, as defined in Sec. 33.75, will be
extremely improbable with a cumulative calculated probability of
failure of less than 10-9 per engine flight hour.
(f) Substantiate by test or analysis that not only will the engine
continue to meet the requirements of Sec. 33.75 following a lightning
strike on the composite fan blade structure, but that the lightning
strike will not cause damage to the fan blades that would prevent
continued safe operation of the affected engine.
(g) Account for the effects of in-service deterioration,
manufacturing variations, minimum material properties, and
environmental effects during the tests and analyses required by
paragraphs (a), (b), (c), (d), (e), and (f) of these special
conditions.
(h) Propose fleet leader monitoring and field sampling programs
that will monitor the effects of engine fan blade usage and fan blade
retention system integrity.
(i) Mark each fan blade legibly and permanently with a part number
and a serial number.
Issued in Burlington, Massachusetts, on June 1, 2015.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2015-14084 Filed 6-8-15; 8:45 am]
BILLING CODE 4910-13-P
