Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72563 

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 

Limitation 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/or 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 10E–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 

October 30, 2015. 

Colleen D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–29589 Filed 11–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3398; Directorate 

Identifier 2015–CE–031–AD; Amendment 

39–18328; AD 2015–16–07 R1] 

RIN 2120–AA64 

Airworthiness Directives; REIMS 

AVIATION S.A. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for REIMS 

AVIATION S.A. Model F406 airplanes. 

This AD revises AD 2015–16–07, which 

required inspection of the left-hand and 

right-hand rudder control pedal torque 

tubes, and, depending on findings, 

replacement with a serviceable part. 

This AD retains the actions of AD 2015– 

16–07 and adds additional acceptable 

serviceable replacement parts. The AD 

was prompted by reports of detachment 

of the pilot’s rudder control pedal in 

flight. We are issuing this AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective December 

28, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of August 18, 2015 (80 FR 

49127). 

We must receive comments on this 

AD by January 4, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact ASI Aviation, 

Ae ́rodrome de Reims Prunay, 51360 

Prunay, FRANCE; telephone: +33 3 26 

48 46 65; fax: +33 3 26 49 18 57; email: 

none; Internet: http://asi-aviation.fr/asiaviation-support/1.html (requires user 

name and password). You may view this 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. It is also available on the Internet 

at http://www.regulations.gov by 

searching for locating Docket No. FAA– 

2015–3398. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3398; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Albert J. Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090; email: 

albert.mercado@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 6, 2015, we issued AD 

2015–16–07, Amendment 39–18232 (80 

FR 49127, August 17, 2015). That AD 

required actions intended to address an 

unsafe condition on REIMS AVIATION 

S.A. Model F406 airplanes and was 

based on mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country. 

Since we issued AD 2015–16–07, 

Amendment 39–18232 (80 FR 49127, 


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72564 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 

August 17, 2015), we received a 

comment from Hageland Aviation 

Services, Inc. requesting that we expand 

what is allowable to use as a 

replacement part for the rudder control 

pedal torque tube as defined in 

paragraph (f)(4) of AD 2015–16–07. The 

commenter requested that we include a 

brand new rudder control pedal that has 

never been installed on an airplane 

because it would have been inspected 

during manufacturing. In addition, 

EASA revised AD 2015–0159–E (2015– 

0159R1) to incorporate the above 

change. 

We agreed with the commenter and 

have revised this AD to add ‘‘a new 

rudder control pedal that has never been 

installed on an airplane’’ to the 

definition of serviceable part. 

Related Service Information Under 1 

CFR Part 51 

ASI AVIATION has issued Service 

Bulletin No.: F406–104, dated July 28, 

2015. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. The service information 

describes procedures for inspection of 

the left-hand and right-hand rudder 

control pedal torque tubes, and, 

depending on findings, replacement 

with a serviceable part. 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 of this AD. 

FAA’s Determination and Requirements 

of the AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that allows 

for the immediate adoption of this AD. 

The FAA has found there is justification 

to waive notice and comment prior to 

adoption of this rule because it only 

changes the definition of a serviceable 

part to give the option of installing a 

new part without inspecting it since it 

already has been inspected at 

manufacture. Therefore, we determine 

that notice and opportunity for public 

comment before issuing this AD are 

unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2014–1123; 

Directorate Identifier 2014–CE–037– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD will affect 7 

products of U.S. registry. We also 

estimate that it will take about 5 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $2,975, or $425 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 20 work-hours and require parts 

costing $10,000, for a cost of $11,700 

per product. We have no way of 

determining the number of products 

that may need these actions. 

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. 

We are 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 

We determined that 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) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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 

■ 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 

removing airworthiness directive (AD) 

2015–16–07 (80 FR 49127, August 17, 

2015) and adding the following new AD: 

2015–16–07 R1 Reims Aviation S.A.: 

Amendment 39–18328; Docket No. 

FAA–2015–3398; Directorate Identifier 

2015–CE–031–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 28, 2015. 

(b) Affected ADs 

This AD replaces AD 2015–16–07, 

Amendment 39–18232 (80 FR 49127, August 

17, 2015) (‘‘AD 2015–16–07’’). 


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Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72565 

(c) Applicability 

This AD applies to Reims Aviation S.A. 

Model F406 airplanes, serial numbers 0001 

through 0098, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as detachment 

of the pilot’s rudder control pedal in flight. 

We are issuing this AD to detect and correct 

cracking of the pilot rudder control pedal 

which, if not corrected, could result in 

detachment of the pedal with possible loss of 

airplane directional control. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraphs (f)(1) through (f)(4) of this AD. 

(1) Before further flight after August 18, 

2015 (the effective date retained from AD 

2015–16–07), do a visual inspection and a 

dye or fluorescent penetrant inspection of the 

rudder control pedal torque tubes, LH (Part 

Number (P/N) 5115260–1) and RH (P/N 

5115260–2), following the instructions of 

PART A of ASI AVIATION Service Bulletin 

No.: F406–104, dated July 28, 2015. 

(2) If no crack is detected during the 

inspection required by paragraph (f)(1) of this 

AD, within 100 hours time-in-service (TIS) 

after August 18, 2015 (the effective date 

retained from AD 2015–16–07), do a 

magnetic particle inspection of the rudder 

control pedal torque tubes, LH (P/N 

5115260–1) and RH (P/N 5115260–2), 

following the instructions of PART B of ASI 

AVIATION Service Bulletin No.: F406–104, 

dated July 28, 2015. 

(3) If any crack is detected on a rudder 

control pedal torque tube during the 

inspection required by paragraph (f)(1) or 

(f)(2) of this AD, before further flight, replace 

the affected part with a serviceable part 

following the instructions of ASI AVIATION 

Service Bulletin No.: F406–104, dated July 

28, 2015. 

(4) For the purpose of this AD, a 

serviceable part is: 

(i) A rudder control pedal torque tube (LH 

P/N 5115260–1 or RH P/N 5115260–2) that 

has had a magnetic particle inspection 

following the instructions of PART B of ASI 

AVIATION Service Bulletin No.: F406–104, 

dated July 28, 2015, and no cracks were 

found; or 

(ii) A new rudder control pedal torque tube 

(LH P/N 5115260–1 or RH P/N 5115260–2) 

that has never been installed on an airplane. 

(5) You may install a rudder control pedal 

torque tube P/N 5115260–1 (LH) or P/N 

5115260–2 (RH) on an airplane, provided it 

is a serviceable part. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Albert J. Mercado, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4119; fax: (816) 

329–4090; email: albert.mercado@faa.gov. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, 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 current 

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 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2015–0159–E, dated 

July 31, 2015, and EASA AD No.: 2015– 

0159R1, dated August 24, 2015, for related 

information. You may examine the MCAI on 

the Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–3398. 

(i) 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. 

(3) The following service information was 

approved for IBR on August 18, 2015 (80 FR 

49127). 

(i) ASI AVIATION Service Bulletin No.: 

F406–104, dated July 28, 2015. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact ASI Aviation, Ae ́rodrome de 

Reims Prunay, 51360 Prunay, FRANCE; 

telephone: +33 3 26 48 46 65; fax: +33 3 26 

49 18 57; email: none; Internet: http://asiaviation.fr/asi-aviation-support/1.html 

(requires user name and password). 

(5) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. It 

is also available on the Internet at http://

www.regulations.gov by searching for 

locating Docket No. FAA–2015–3398. 

(6) 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, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on 

November 6, 2015. 

Melvin Johnson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–29200 Filed 11–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0427; Directorate 

Identifier 2013–NM–218–AD; Amendment 

39–18316; AD 2015–22–11] 

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) 2011–09– 

04 for all Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company 

Model 382, 382B, 382E, 382F, and 382G 

airplanes. AD 2011–09–04 required 

repetitive inspections for damage to the 

lower surface of the center wing box 

(CWB), and corrective actions if 

necessary. This new AD adds related 

investigative actions, and corrective 

actions if necessary. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) that 

indicated that the CWB is subject to 

widespread fatigue damage (WFD). We 

are issuing this AD to detect and correct 

fatigue cracking of the lower surface of 

the CWB, which could result in 

structural failure of the wings. 

DATES: This AD is effective December 

28, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 


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