32440 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 

Accordingly, 7 CFR part 633 is 

amended as follows: 

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. 

* * * * * 

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. 

* * * * * 

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: 

§ 633.4 Program requirements. 

* * * * * 

(d) * * * 

(2) Lands owned by an agency of the 

United States other than land held in 

trust for Indian Tribes; 

* * * * * 

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 

[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 

§ 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. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 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 

§ 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 § 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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: 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 


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