This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

1291 

Vol. 81, No. 7 

Tuesday, January 12, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6823; Directorate 

Identifier 2015–NE–38–AD; Amendment 39– 

18360; AD 2015–27–01] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

General Electric Company (GE) GE90– 

76B, –77B, –85B, –90B, and –94B 

turbofan engines. This AD requires 

performing an eddy current inspection 

(ECI) or ultrasonic inspection (USI) of 

the high-pressure compressor (HPC) 

stage 8–10 spool and removing from 

service those parts that fail inspection. 

This AD was prompted by an 

uncontained failure of the HPC stage 8– 

10 spool, leading to an airplane fire. We 

are issuing this AD to prevent failure of 

the HPC stage 8–10 spool, uncontained 

rotor release, damage to the engine, and 

damage to the airplane. 

DATES: This AD is effective January 27, 

2016. 

We must receive comments on this 

AD by February 26, 2016. 

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: 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. 

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– 

6823; 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 (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: John 

Frost, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7756; fax: 781–238– 

7199; email: john.frost@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report of an HPC stage 

8–10 spool uncontained failure resulting 

in an airplane fire. Ongoing 

investigations have determined that a 

crack initiated in the stage 8 aft web 

upper face of the HPC 8–10 spool and 

propagated until spool rupture. The root 

cause of the crack initiation is not yet 

known. This condition, if not corrected, 

could result in failure of the HPC stage 

8–10 spool, uncontained rotor release, 

damage to the engine, and damage to the 

airplane. We are issuing this AD to 

correct the unsafe condition on these 

products. 

Related Service Information 

We reviewed GE Service Bulletin (SB) 

No. GE90 S/B 72–1145, dated November 

24, 2015. The SB describes procedures 

for one-time on-wing USI of the stage 8 

web of the stage 8–10 spool. We also 

reviewed the following chapters of GE 

GE90 Engine Manual, GEK100700, 

Revision 66, dated September 1, 2015: 

• Chapter 72–31–08, Special 

Procedure 003, piece-part level ECI, 

• Chapter 72–00–31, Special 

Procedure 006, rotor assembly and 

module level ECI and, 

• Chapter 72–00–31, Special 

Procedure 007, rotor assembly level USI. 

FAA’s Determination 

We are issuing 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. 

AD Requirements 

This AD requires accomplishing an 

ECI or USI of the stage 8 aft web upper 

face of the HPC stage 8–10 spool and 

removing from service those parts that 

fail inspection. 

Interim Action 

We consider this AD interim action. 

GE is determining the root cause for the 

unsafe condition identified in this AD. 

Once a root cause is identified, we 

might consider additional rulemaking. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule based on the reported engine 

failure. Therefore, we find that notice 

and opportunity for prior public 

comment are impracticable and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–6823; Directorate Identifier 2015– 

NE–38–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. 


tkelley on DSK3SPTVN1PROD with RULES
1292 Federal Register / Vol. 81, No. 7 / Tuesday, January 12, 2016 / Rules and Regulations 

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 affects 1 

engine installed on an airplane of U.S. 

registry. We also estimate that it will 

take about 7 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Required parts cost about 

$780,000 per engine. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $780,595. 

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 

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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, 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 adding 

the following new airworthiness 

directive (AD): 

2015–27–01 General Electric Company: 

Amendment 39–18360; Docket No. 

FAA–2015–6823; Directorate Identifier 

2015–NE–38–AD. 

(a) Effective Date 

This AD is effective January 27, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GE90–76B, –77B, –85B, –90B, 

and –94B turbofan engines with highpressure compressor (HPC) stage 8–10 spool, 

part number 1694M80G04, installed. 

(d) Unsafe Condition 

This AD was prompted by an uncontained 

failure of the HPC stage 8–10 spool, leading 

to an airplane fire. We are issuing this AD to 

prevent failure of the HPC stage 8–10 spool, 

uncontained rotor release, damage to the 

engine, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Perform an eddy current inspection or 

ultrasonic inspection of the stage 8 aft web 

upper face of the HPC stage 8–10 spool for 

cracks as follows: 

(i) For HPC stage 8–10 spools with serial 

number (S/N) GWNHC086 or GWNHB875, 

inspect within 150 cycles-in-service (CIS), 

after the effective date of this AD. 

(ii) For HPC stage 8–10 spools with S/N 

GWNHC154, GWNHA455, GWNHC153, or 

GWNHB516, inspect within 300 CIS, after the 

effective date of this AD. 

(2) Remove from service any HPC stage 8– 

10 spool that fails the inspection required by 

paragraph (e)(1) of this AD and replace the 

spool with a spool eligible for installation. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(g) Related Information 

For more information about this AD, 

contact John Frost, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7756; fax: 781–238–7199; 

email: john.frost@faa.gov. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

December 21, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–33075 Filed 1–11–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 61 and 183 

[Docket No.: FAA–2010–1127; Amdt. Nos. 

61–135 and 183–15] 

RIN 2120–AJ42 

Student Pilot Application 

Requirements 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action requires 

applicants to apply for a student pilot 

certificate through a Flight Standards 

District Office, designated pilot 

examiner, airman certification 

representative associated with a pilot 

school, or certified flight instructor. 

Aviation Medical Examiners will no 

longer issue a combination medical 

certificate and student pilot certificate. 

Student pilot certificates will be issued 

on the same medium as other pilot 

certificates and will have no expiration 

date. All student pilot certificates issued 

before the effective date of this final rule 

will expire according to their terms 

unless they are replaced by another 

pilot certificate. This final rule responds 

to section 4012 of the Intelligence 

Reform and Terrorism Prevention Act 

and facilitates security vetting by the 

Transportation Security Administration 

of student pilot applicants prior to 

certificate issuance. This action 

withdraws the proposal for pilot 

certificates to include a photograph of 

the individual pilot. Section 321 of the 

FAA Modernization and Reform Act of 

2012 supersedes section 4022 of the 

Intelligence Reform and Terrorism 

Prevention Act, which provided the 


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