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

27069 

Vol. 80, No. 91 

Tuesday, May 12, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1278; Directorate 

Identifier 2014–NM–223–AD; Amendment 

39–18155; AD 2015–09–09] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2004–07– 

11 for all The Boeing Company Model 

767–400ER series airplanes. AD 2004– 

07–11 requires repetitive high frequency 

eddy current (HFEC) inspections of the 

aft lower lugs of the deflection control 

track of the outboard flap for cracks, and 

replacement of any cracked deflection 

control track with a new track assembly. 

This AD retains those requirements, 

provides optional terminating action for 

the repetitive inspections, and adds 

airplane models to the applicability. 

This AD was prompted by our 

determination that additional airplane 

models require repetitive HFEC 

inspections of the aft lower lugs of the 

deflection control track of the outboard 

flap for cracks, and replacement of any 

cracked deflection control track with a 

new track assembly. We are issuing this 

AD to detect and correct fatigue 

cracking in the aft lower lug run-out 

region of the deflection control track, 

which could result in the loss of the 

secondary load path for the outboard 

flap, resulting in the loss of the outboard 

flap and consequent reduced 

controllability of the airplane in the 

event that the primary load path also 

fails. 

DATES: This AD is effective May 27, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 27, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 11, 2004 (69 FR 

17911, April 6, 2004). 

We must receive any comments on 

this AD by June 26, 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: 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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https://

www.myboeingfleet.com. 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1278. 

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– 

1278; 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6577; 

fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 22, 2004, we issued AD 

2004–07–11, Amendment 39–13555 (69 

FR 17911, April 6, 2004), for all The 

Boeing Company Model 767–400ER 

series airplanes. AD 2004–07–11 

required repetitive HFEC inspections of 

the aft lower lugs of the deflection 

control track of the outboard flap for 

cracks, and replacement of any cracked 

deflection control track with a new track 

assembly. AD 2004–07–11 resulted from 

reports of fatigue cracking in the aft 

lower lug run-out region of the 

deflection control track. We issued AD 

2004–07–11 to detect and correct fatigue 

cracking of the deflection control track, 

which could result in the loss of the 

secondary load path for the outboard 

flap, resulting in the loss of the outboard 

flap and consequent reduced 

controllability of the airplane in the 

event that the primary load path also 

fails. 

Actions Since AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, 

April 6, 2004) Was Issued 

Since we issued AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, 

April 6, 2004), we have determined that 

additional airplane models are subject 

to the identified unsafe condition. The 

flap installations on certain Model 767– 

200 and –300 series airplanes, serial 

numbers 922 through 933 inclusive, are 

identical to those installed on Model 

767–400ER series airplanes. Therefore, 

all of these models may be subject to the 

identified unsafe condition. We are 

issuing this AD to detect and correct 

fatigue cracking in the aft lower lug runout region of the deflection control 

track, which could result in the loss of 

the secondary load path for the outboard 

flap, resulting in the loss of the outboard 

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27070 Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Rules and Regulations 

flap and consequent reduced 

controllability of the airplane in the 

event that the primary load path also 

fails, on certain Model 767–200 and 

–300 series airplanes, serial numbers 

922 through 933 inclusive. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Service Bulletin 

767–27A0183, Revision 2, dated 

September 25, 2014. The service 

information describes procedures for 

repetitive HFEC inspections of the aft 

lower lugs of the deflection control track 

of the outboard flap for cracks, and 

replacement of any cracked deflection 

control track with a new track assembly, 

part number 113T8333–9, which 

eliminates the need for the repetitive 

HFEC inspections. This service 

information is reasonably available at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

1278. Or see ADDRESSES for other ways 

to access this service information. 

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 retains all of the 

requirements of AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, 

April 6, 2004). This AD continues to 

require repetitive HFEC inspections of 

the aft lower lugs of the deflection 

control track of the outboard flap for 

cracks, and replacement of any cracked 

deflection control track with a new track 

assembly. This AD adds airplane 

models to the applicability, and 

provides optional terminating action for 

the repetitive HFEC inspections even if 

no crack is found. 

Change to AD 2004–07–11, Amendment 

39–13555 (69 FR 17911, April 6, 2004) 

Since AD 2004–07–11, Amendment 

39–13555 (69 FR 17911, April 6, 2004) 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. As a result, the 

corresponding paragraph designations 

have been redesignated in this AD, as 

listed in the following table: 

REVISED PARAGRAPH DESIGNATIONS

Requirement in AD 

2004–07–11, Amendment 39–13555 (69 

FR 17911, April 6, 

2004) 

Corresponding 

requirement 

in this AD 

paragraph (a) paragraph (g) 

paragraph (b) paragraph (h) 

paragraph (c) paragraph (i) 

Clarification of Paragraph (c) of AD 

2004–07–11, Amendment 39–13555 (69 

FR 17911, April 6, 2004) 

We have added a reference to 

paragraph (h) of this AD to the 

corrective action requirements of 

paragraph (i) of this AD (which we 

referred to as paragraph (c) of AD 2004– 

07–11, Amendment 39–13555 (69 FR 

17911, April 6, 2004)). We have made 

this change to clarify the corrective 

action. 

FAA’s Justification and Determination 

of the Effective Date 

This AD revises the applicability by 

adding airplanes that are not on the U.S. 

Register. Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary 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 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

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– 

1278 and directorate identifier 2014– 

NM–223–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 

The actions specified by this AD were 

previously required by AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, 

April 6, 2004), which was applicable to 

approximately 38 airplanes. The actions 

required by AD 2004–07–11 take about 

5 work-hours per airplane. In 

consideration of the compliance time 

and effective date of AD 2004–07–11, 

we assume that operators of the 38 

airplanes subject to that AD have 

already initiated the required actions. 

This AD would add no new costs 

associated with the airplanes of U.S. 

registry, but would be applicable to 

approximately 11 additional airplanes 

of the affected design in the worldwide 

fleet. The current costs for this AD are 

repeated for the convenience of affected 

operators, as follows: 

ESTIMATED COSTS—REQUIRED ACTIONS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Retained inspections from AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, April 6, 

2004).

5 work-hours × $85 per 

hour = $425 per inspection cycle.

$0 $425 per inspection 

cycle.

$16,150 per inspection 

cycle. 

We estimate that it would take about 

12 work-hours to do any necessary 

replacement that would be required 

based on the results of the inspection. 

We have received no definitive data that 

would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. We have no way 

of determining the number of aircraft 

that might 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 

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Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Rules and Regulations 27071 

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, 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 part 39 of the Federal 

Aviation Regulations (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) 

2004–07–11, Amendment 39–13555 (69 

FR 17911, April 6, 2004) and adding the 

following new AD: 

2015–09–09 The Boeing Company: 

Amendment 39–18155; Docket No. 

FAA–2015–1278; Directorate Identifier 

2014–NM–223–AD. 

(a) Effective Date 

This AD is effective May 27, 2015. 

(b) Affected ADs 

This AD replaces AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, April 6, 

2004). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, -300, and -400ER series 

airplanes, certificated in any category, as 

identified in Boeing Service Bulletin 767– 

27A0183, Revision 2, dated September 25, 

2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls; 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by our 

determination that additional airplane 

models require repetitive high frequency 

eddy current (HFEC) inspections of the aft 

lower lugs of the deflection control track of 

the outboard flap for cracks, and replacement 

of any cracked deflection control track with 

a new track assembly. We are issuing this AD 

to detect and correct fatigue cracking in the 

aft lower lug run-out region of the deflection 

control track, which could result in the loss 

of the secondary load path for the outboard 

flap, resulting in the loss of the outboard flap 

and consequent reduced controllability of the 

airplane in the event that the primary load 

path also fails. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Initial Inspection for Model 

767–400ER Series Airplanes 

This paragraph restates the requirements of 

paragraph (a) of AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, April 6, 

2004), with revised service information. For 

airplanes identified in Group 1 in Boeing 

Service Bulletin 767–27A0183, Revision 2, 

dated September 25, 2014: Before the 

accumulation of 12,000 total flight cycles, or 

within 1,200 flight cycles after May 11, 2004 

(the effective date of AD 2004–07–11), 

whichever occurs later, perform an HFEC 

inspection for cracks in the aft lower lug of 

the deflection control track on the outboard 

flap, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–27A0183, dated May 9, 2002; or Boeing 

Service Bulletin 767–27A0183, Revision 2, 

dated September 25, 2014. As of the effective 

date of this AD, only Boeing Service Bulletin 

767–27A0183, Revision 2, dated September 

25, 2014, may be used. 

(h) Retained Repetitive Inspections With 

New Service Information 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, April 6, 

2004), with new service information. For 

airplanes identified in Group 1 in Boeing 

Service Bulletin 767–27A0183, Revision 2, 

dated September 25, 2014: If no crack is 

detected during any HFEC inspection 

required in paragraph (g) of this AD, repeat 

the inspection at intervals not to exceed 

1,200 flight cycles. 

(i) Retained Corrective Action and Added 

Terminating Action 

This paragraph restates the requirements of 

paragraph (c) of AD 2004–07–11, 

Amendment 39–13555 (69 FR 17911, April 6, 

2004), with revised service information, 

added terminating action, and added 

paragraph reference. For airplanes identified 

in Group 1 in Boeing Service Bulletin 767– 

27A0183, Revision 2, dated September 25, 

2014: If any crack is detected during any 

HFEC inspection required by paragraph (g) or 

(h) of this AD, before further flight, replace 

the deflection control track with a new track 

assembly, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–27A0183, dated May 9, 

2002; or Boeing Service Bulletin 767– 

27A0183, Revision 2, dated September 25, 

2014. Within 12,000 flight cycles following 

the replacement of deflection control track 

with a deflection control track, part number 

(P/N) 113T7333–3 or 113T8333–7, perform 

the HFEC inspection specified in paragraph 

(g) of this AD, and repeat inspections as 

specified in paragraph (h) of this AD until the 

deflection control track is replaced with a 

deflection control track, P/N 113T8333–9, as 

specified in paragraph (m) of this AD. As of 

the effective date of this AD, only Boeing 

Service Bulletin 767–27A0183, Revision 2, 

dated September 25, 2014, may be used. 

(j) New Initial Inspection for Model 767–200 

and –300 Series Airplanes 

For airplanes identified in Group 2 in 

Boeing Service Bulletin 767–27A0183, 

Revision 2, dated September 25, 2014: Before 

the accumulation of 12,000 total flight cycles, 

or within 1,200 flight cycles after the 

effective date of this AD, whichever occurs 

later, do an HFEC inspection for cracks in the 

aft lower lug of the deflection control track 

on the outboard flap, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27A0183, Revision 2, 

dated September 25, 2014. 

(k) New Repetitive Inspections 

For airplanes identified in Group 2 in 

Boeing Service Bulletin 767–27A0183, 

Revision 2, dated September 25, 2014: If no 

crack is detected during any HFEC inspection 

required in paragraph (j) of this AD, repeat 

the inspection thereafter at intervals not to 

exceed 1,200 flight cycles. 

(l) New Corrective Action and Terminating 

Action 

For airplanes identified in Group 2 in 

Boeing Service Bulletin 767–27A0183, 

Revision 2, dated September 25, 2014: If any 

crack is detected during any HFEC inspection 

required by paragraph (j) or (k) of this AD, 

before further flight, replace the deflection 

control track with a new track assembly, part 

number 113T8333–9, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27A0183, Revision 2, 

dated September 25, 2014. This replacement 

terminates the inspection requirements of 

paragraphs (j) and (k) of this AD. 

(m) Optional Terminating Action 

Replacement of the deflection control track 

with a new track assembly, P/N 113T8333– 

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27072 Federal Register / Vol. 80, No. 91 / Tuesday, May 12, 2015 / Rules and Regulations 

9, in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

27A0183, Revision 2, dated September 25, 

2014, terminates the inspection requirements 

of paragraphs (g), (h), (j), and (k) of this AD. 

(n) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (g), (h), (i), 

and (m) of this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Service Bulletin 767–27A0183, 

Revision 1, dated April 4, 2014, which is not 

incorporated by reference in this AD. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (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 (p)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(p) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6577; fax: 425–917–6590; 

email: berhane.alazar@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (q)(5) and (q)(6) of this AD. 

(q) 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 May 27, 2015. 

(i) Boeing Service Bulletin 767–27A0183, 

Revision 2, dated September 25, 2014. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 11, 2004, (69 FR 

17911, April 6, 2004). 

(i) Boeing Alert Service Bulletin 767– 

27A0183, dated May 9, 2002. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(6) You may view this service information 

at 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. 

(7) 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 Renton, Washington, on April 29, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–11137 Filed 5–11–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0415; Directorate 

Identifier 2015–CE–001–AD; Amendment 

39–18152; AD 2015–09–06] 

RIN 2120–AA64 

Airworthiness Directives; GROB– 

WERKE Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–26– 

04 for certain GROB–WERKE Models 

G115EG and G120A airplanes. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued 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 a defective starter solenoid. 

We are issuing this AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective June 16, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 16, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of February 9, 2015 (80 FR 

155, January 5, 2015). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0415; or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

For service information identified in 

this AD, contact Grob Aircraft AG, 

Customer Service, Lettenbachstrasse 9, 

D–86874 Tussenhausen-Mattsies, 

Germany, telephone: + 49 (0) 8268–998– 

105; fax: + 49 (0) 8268–998–200; email: 

productsupport@grob-aircraft.com; 

Internet: grob-aircraft.com. 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 

and locating Docket No. FAA–2015– 

0415. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to certain GROB–WERKE Models 

G115EG and G120A airplanes. That 

NPRM was published in the Federal 

Register on February 26, 2015 (80 FR 

10423), and proposed to supersede AD 

2014–26–04, Amendment 39–18055 (80 

FR 155, January 5, 2015). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products and was based on mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country. The MCAI 

states: 

An operator of a G 115E aeroplane 

experienced a total loss of electrical power in 

flight. The investigation found that a 

defective starter solenoid had caused an 

internal short circuit which resulted in 

breakdown of the system voltage. 

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