Federal Register / Vol. 80, No. 102 / Thursday, May 28, 2015 / Proposed Rules 30391 

List of Subjects in 14 CFR Part 33 

Air Transportation, Aircraft, Aviation, 

Aviation safety, Safety. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Proposed Special Conditions 

Accordingly, the Federal Aviation 

Administration (FAA) proposes the 

following special conditions as part of 

the type certification basis for Pratt and 

Whitney Canada PW210A engine 

model. 

Flat 30-Second and 2-Minute OEI 

1. Part 1.1 Definitions 

‘‘Rated Flat 30-second and 2-minute 

One Engine Inoperative (OEI) Power,’’ 

with respect to rotorcraft turbine 

engines, means (1) a single rating for 

which the shaft horsepower and 

associated operating limitations of the 

30-second OEI and 2-minute OEI ratings 

are equal, and (2) the shaft horsepower 

is that developed under static 

conditions at the altitude and 

temperature for the hot day, and within 

the operating limitations established 

under Part 33. The rating is for 

continuation of flight operation after the 

failure or shutdown of one engine in 

multiengine rotorcraft, for up to three 

periods of use no longer than 2.5 

minutes each in any one flight, and 

followed by mandatory inspection and 

prescribed maintenance action. 

2. Part 33 Requirements 

(a) The airworthiness standards in 

Part 33 Amendment 30 for the 30- 

second OEI and 2-minute OEI ratings 

are applicable to the Flat 30-second and 

2-minute OEI Power rating. In addition 

the following special conditions apply; 

(b) Section 33.7 Engine ratings and 

operating limitations. Flat 30-second 

and 2-minute OEI Power rating and 

operating limitations are established for 

power, torque, rotational speed, gas 

temperature, and time duration. 

(c) Section 33.27 Turbine, 

compressor, fan, and turbosupercharger 

rotor overspeed. The requirements of 

§ 33.27, except that following the test, 

the rotor may not exhibit conditions 

such as cracking or distortion which 

preclude continued safe operation. 

(d) Section 33.28 Engine controls 

systems. Must incorporate a means, or a 

provision for a means, for automatic 

availability and automatic control of the 

Flat 30-second and 2-minute OEI Power 

within the declared operating 

limitations. 

(e) Section 33.29 Instrument 

Connection. In lieu of the requirements 

of 33.29(c) the PW210A must 

incorporate a means or a provision for 

a means to: 

(1) Alert the pilot when the engine is 

at the Flat 30-second and 2-minute OEI 

Power level, when the event begins, and 

when the time interval expires; 

(2) Automatically record each usage 

and duration of power at the Flat 30- 

second and 2-minute OEI Power rating; 

(3) Following each flight when the 

Flat 30-second and 2-minute OEI Power 

rating is used, alert maintenance 

personnel in a positive manner that the 

engine has been operated at the Flat 30- 

second and 2-minute OEI Power level, 

and permit retrieval of the recorded 

data; and 

(4) Enable routine verification of the 

proper operation of the above means. 

(f) Section 33.87 Endurance test. The 

requirements applicable to 30-second 

and 2-minute OEI ratings, except for: 

(1) The test of § 33.87(a)(7) for the 

purposes of temperature stabilization, 

must be run with a test period time of 

2.5 minutes. 

(2) The tests in § 33.87(f)(2) and (3) 

must be run continuously for the 

duration of 2.5 minutes, and 

(3) The tests in § 33.87(f)(6) and (7) 

must be run continuously for the 

duration of 2.5 minutes. 

(g) Section 33.88 Engine 

overtemperature test. The requirements 

of § 33.88(b) except that the test time is 

5 minutes instead of 4 minutes. 

Issued in Burlington, Massachusetts, on 

May 18, 2015. 

Carlos Pestana, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–12986 Filed 5–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1425; Directorate 

Identifier 2014–NM–185–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

188 series airplanes. This proposed AD 

was prompted by an evaluation by the 

design approval holder (DAH) 

indicating that a certain circumferential 

fuselage splice is subject to widespread 

fatigue damage (WFD). This proposed 

AD would require an inspection for 

corrosion and previous repairs, severed 

stringers, cracking, and loose or 

distressed fasteners of the forward and 

aft ends of the stringer splices of certain 

stringers, inspection for cracking and 

modification of certain fastener holes 

common to the stringer and splice 

member at the forward and aft ends of 

the splice, and related investigative and 

corrective actions if necessary. We are 

proposing this AD to prevent loss of 

residual strength of a certain 

circumferential fuselage splice, which 

could lead to rapid decompression of 

the cabin and potential loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by July 13, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, GA 

30063; phone: 770–494–5444; fax: 770– 

494–5445; email: ams.portal@lmco.com; 

Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. You may view this 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

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– 

1425; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 


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except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Carl 

Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, GA 

30337; phone: 404–474–5554; fax: 404– 

474–5605; email: carl.w.gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–1425; Directorate Identifier 2014– 

NM–185–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as WFD. As an 

airplane ages, WFD will likely occur, 

and will certainly occur if the airplane 

is operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

This proposed AD was prompted by 

an evaluation by the DAH indicating 

that the circumferential fuselage splice 

at fuselage-station (FS) 695 is subject to 

WFD. The root cause of this WFD is 

fatigue cracks manifesting and growing 

simultaneously at similar structural 

details and stress levels at the 

circumferential fuselage splice. Fatigue 

cracking is increasingly likely as the 

airplane is operated and aged, and 

without intervention, fatigue cracking 

could lead to loss of residual strength of 

the circumferential fuselage splice at FS 

695, which could lead to rapid 

decompression of the cabin area and 

potential loss of the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Lockheed Martin Electra 

Service Bulletin 88/SB–722, dated April 

30, 2014. This service bulletin describes 

procedures for doing the following 

actions: 

• A general visual inspection (GVI) 

for corrosion and previous repairs, 

severed stringers, cracking, and loose or 

distressed fasteners of the forward and 

aft ends of the stringer splices of 

stringers 1–7 and 66–72, and corrective 

actions if necessary. 

• At stringers 1–7 and 66–72, 

removing the four rivets common to the 

stringer and splice member at the 

forward and aft ends of the splice and 

doing a bolt hole eddy current (BHEC) 

inspection or an equivalent inspection 

procedure for cracking in each of the 

fastener holes, and corrective actions if 

necessary. 

• Corrective actions for cracked holes 

include reaming to the maximum 

permissible hole diameter of the next 

larger size rivet. If a crack indication 

remains after reaming, this service 

information specifies repairing the 

cracked stringer. 

• If a severed stringer is found during 

the GVI, doing related investigative 

actions of an eddy current surface scan 

inspection for cracking of the fuselage 

skin at the skin-to-stringer attachments 

immediately forward and aft of the 

stringer break and confirming skin 

cracks with a dye penetrant inspection. 

Corrective actions include repairing the 

severed stringer or skin cracks. 

• For holes without crack indications, 

other specified actions include 

modifying the fastener holes by reaming 

to a certain maximum permissible hole 

diameter of the same size rivet and 

installing replacement fasteners; or if 

original hole is larger than the 

maximum permissible diameter, 

installing the next rivet size and type. 

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 NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 


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previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ 

Differences Between This Proposed AD 

and the Service Information 

Although Lockheed Martin Electra 

Service Bulletin 88/SB–722, dated April 

30, 2014, specifies that crack indications 

should be confirmed by an alternate 

inspection method, this proposed AD 

would not require that action. 

Operators should note that, although 

the Accomplishment Instructions of 

Lockheed Martin Electra Service 

Bulletin 88/SB–722, dated April 30, 

2014, describe procedures for 

submitting a report of damage, this 

proposed AD would not require that 

action. 

Lockheed Martin Electra Service 

Bulletin 88/SB–722, dated April 30, 

2014, does not describe corrective 

actions if any corrosion or previous 

repair is found, and if any loose or 

distressed fastener is found. This 

proposed AD would require repair. 

Explanation of Proposed Compliance 

Time 

The compliance time for the 

modification specified in this proposed 

AD for addressing WFD was established 

to ensure that discrepant structure is 

replaced before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. We will not grant any extensions 

of the compliance time to complete any 

AD-mandated service bulletin related to 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspections and Modification .......................... 18 work-hours × $85 per hour = $1,530 ........ $5,000 $6,530 $26,120 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company: Docket 

No. FAA–2015–1425; Directorate 

Identifier 2014–NM–185–AD. 

(a) Comments Due Date 

We must receive comments by July 13, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company Model 188A and 188C airplanes, 

certificated in any category, serial numbers 

1001 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the circumferential fuselage splice at 

fuselage-station (FS) 695 is subject to 

widespread fatigue damage (WFD). We are 

issuing this AD to prevent loss of residual 

strength of the circumferential fuselage splice 

at FS 695, which could lead to rapid 

decompression of the cabin and potential 

loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections, Modification, Related 

Investigative Actions, and Corrective 

Actions 

Before the accumulation of 38,200 total 

flight hours or within 30 days after the 

effective date of this AD, whichever occurs 

later: Do a general visual inspection for 

corrosion and previous repairs, severed 

stringers, cracking, and loose or distressed 

fasteners of the forward and aft ends of the 

stringer splices of stringers 1–7 and 66–72; 

remove the four rivets common to the 

stringer and splice member at the forward 

and aft ends of the splice and do a bolt hole 

eddy current inspection or an equivalent 

inspection procedure for cracking in each of 

the fastener holes; modify the fastener holes; 


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30394 Federal Register / Vol. 80, No. 102 / Thursday, May 28, 2015 / Proposed Rules 

and do all applicable related investigative 

and corrective actions and other specified 

actions; in accordance with the 

Accomplishment Instructions of Lockheed 

Martin Electra Service Bulletin 88/SB–722, 

dated April 30, 2014, except as specified in 

paragraph (h) of this AD. Do all applicable 

related investigative and corrective actions 

and other specified actions before further 

flight. If any repairs exceed the repair limits 

specified in Lockheed Martin Electra Service 

Bulletin 88/SB–722, dated April 30, 2014, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(h) Corrective Action 

(1) If, during any inspection required by 

paragraph (g) of this AD, any corrosion or 

previous repair is found, before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(2) If, during any inspection required by 

paragraph (g) of this AD, any loose or 

distressed fastener is found, before further 

flight, repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(i) Exception 

Although Lockheed Martin Electra Service 

Bulletin 88/SB–722, dated April 30, 2014, 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta ACO, 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 ACO, send it to the 

attention of the person identified in 

paragraph (j)(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. 

(k) Related Information 

(1) For more information about this AD, 

Carl Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta ACO, 1701 

Columbia Avenue, College Park, GA 30337; 

phone: 404–474–5554; fax: 404–474–5605; 

email: carl.w.gray@faa.gov. 

(2) For service information identified in 

this AD, contact Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company, Airworthiness Office, Dept. 6A0M, 

Zone 0252, Column P–58, 86 S. Cobb Drive, 

Marietta, GA 30063; phone: 770–494–5444; 

fax: 770–494–5445; email: ams.portal@

lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. You may view this service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on May 19, 

2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–12859 Filed 5–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 91 

[Docket No.: FAA–2015–1746; Notice No. 

15–05] 

RIN 2120–AK54 

Changes to the Application 

Requirements for Authorization to 

Operate in Reduced Vertical 

Separation Minimum Airspace 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action would revise the 

FAA’s requirements for an application 

to operate in Reduced Vertical 

Separation Minimum (RVSM) airspace. 

This proposal would eliminate the 

burden and expense of developing, 

processing, and approving RVSM 

maintenance programs. As a result of 

this proposed revision, an applicant to 

operate in RVSM airspace would no 

longer be required to develop and 

submit an RVSM maintenance program 

solely for the purpose of an RVSM 

authorization. Because of other, 

independent FAA airworthiness 

regulations, all aircraft operators would 

nevertheless continue to be required to 

maintain RVSM equipment in an 

airworthy condition. 

DATES: Send comments on or before July 

27, 2015. 

ADDRESSES: Send comments identified 

by docket number FAA–2015–1746 

using any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: In accordance with 5 U.S.C. 

553(c), DOT solicits comments from the 

public to better inform its rulemaking 

process. DOT posts these comments, 

without edit, including any personal 

information the commenter provides, to 

www.regulations.gov, as described in 

the system of records notice (DOT/ALL– 

14 FDMS), which can be reviewed at 

www.dot.gov/privacy. 

Docket: Background documents or 

comments received may be read at 

http://www.regulations.gov at any time. 

Follow the online instructions for 

accessing the docket or go to Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Charles Fellows, 

Aviation Safety Inspector, Avionics 

Branch, Aircraft Maintenance Division, 

Flight Standards Services, AFS–360, 

Federal Aviation Administration, 950 

L’Enfant Plaza North SW., Washington, 

DC 20024; telephone (202) 267–1706; 

email Charles.Fellows@faa.gov. 

For legal questions concerning this 

action, contact Benjamin Jacobs, 

Attorney-Advisor, Office of Chief 

Counsel, AGC–200, Federal Aviation 

Administration, 800 Independence Ave. 

SW., Washington, DC 20591; telephone 

(202) 267–7240; email 

Benjamin.Jacobs@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

Sections 106(f), 40113, and 44701 

authorize the FAA Administrator to 

prescribe regulations necessary for 

aviation safety. Section 40103 

authorizes the Administrator to 

prescribe regulations to enhance the 

efficiency of the national airspace. This 

rulemaking is within the scope of these 

authorities because it would remove 

existing safety and airspace-related 

regulations that the FAA no longer finds 

necessary to protect aviation safety. 

I. Executive Summary 

A. Summary of Proposed Rule 

This Notice of Proposed Rulemaking 

(NPRM) proposes to remove the 

requirement in Appendix G of part 91 

of Title 14 of the Code of Federal 

Regulations (14 CFR) that any operator 

seeking Reduced Vertical Separation 

Minimum (RVSM) authorization must 


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