76878 Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules 

on which the modification described in 

Airbus Service Bulletin A330–36–3032 has 

not been incorporated, and for Model A340 

series airplanes: Doing the bleed leak 

detection loop modification of the APU, in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

bulletin specified in paragraphs (i)(1) and 

(i)(2) of this AD, is an acceptable alternative 

to the actions required by paragraph (h) of 

this AD, provided the modification is 

accomplished within 26 months after March 

26, 2014 (the effective date of AD 2014–03– 

14). 

(1) Airbus Service Bulletin A330–36–3037, 

Revision 02, dated April 7, 2014. 

(2) Airbus Service Bulletin A340–36–4033, 

Revision 02, dated May 19, 2014. 

(j) Retained Drain Mast Installation, With No 

Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2014–03–14, Amendment 

39–17752 (79 FR 9382, February 19, 2014), 

with no changes. For Model A340–500 and 

–600 series airplanes, except those on which 

Airbus Modification 54636 or 54637 has been 

incorporated in production: Within 26 

months after March 26, 2014 (the effective 

date of AD 2014–03–14), install a drain mast 

between frame (FR) 80 and FR 83, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–53–5031, Revision 02, dated 

August 3, 2011. 

(k) New Requirement of This AD: 

Replacement of Certain Insulation Sleeves 

For Model A340 series airplanes in 

configurations 002, 003, and 005, as 

described in Airbus Service Bulletin A340– 

36–4035, dated September 18, 2012, that 

have been modified before the effective date 

of this AD in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–36–4035, dated 

September 18, 2012: Within 14 months after 

the effective date of this AD, replace the 

insulation sleeves between frames 83 and 84 

with new insulation sleeves, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A340–36–4035, 

Revision 01, dated September 24, 2013. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before March 

26, 2014 (the effective date of AD 2014–03– 

14, Amendment 39–17752 (79 FR 9382, 

February 19, 2014)), using Airbus Service 

Bulletin A330–33–3041, dated January 3, 

2012; or Airbus Service Bulletin A340–33– 

4026, dated January 3, 2012; as applicable; 

which are not incorporated by reference in 

this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before March 

26, 2014 (the effective date of AD 2014–03– 

14, Amendment 39–17752 (79 FR 9382, 

February 19, 2014)), using Airbus Service 

Bulletin A330–36–3040, dated September 18, 

2012, which is not incorporated by reference 

in this AD. 

(3) For Model A340 series airplanes in 

configurations 001 and 004, as described in 

Airbus Service Bulletin A340–36–4035, 

dated September 18, 2012: This paragraph 

provides credit for actions required by 

paragraph (h) of this AD, if those actions 

were performed before the effective date of 

this AD using Airbus Service Bulletin A340– 

36–4035, dated September 18, 2012, which is 

not incorporated by reference in this AD. 

(4) This paragraph provides credit for 

actions required by paragraph (j) of this AD, 

if those actions were performed before March 

26, 2014 (the effective date of AD 2014–03– 

14, Amendment 39–17752 (79 FR 9382, 

February 19, 2014)), using Airbus Service 

Bulletin A340–53–5031, dated July 31, 2006; 

or Airbus Service Bulletin A340–53–5031, 

Revision 01, dated January 10, 2008; as 

applicable; which are not incorporated by 

reference in this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) 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. The AMOC 

approval letter must specifically reference 

this AD. 

(ii) AMOCs approved previously for 

paragraphs (g) and (h) of AD 2014–03–14, 

Amendment 39–17752 (79 FR 9382, February 

19, 2014), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

and (h) of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0148, dated 

June 13, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2015–6547. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. 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 

December 4, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–31210 Filed 12–10–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6548; Directorate 

Identifier 2015–NM–114–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

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 

The Boeing Company Model 787–8 and 

787–9 airplanes equipped with General 

Electric engines. This proposed AD was 

prompted by reports of cracking in 

barrel nuts on a forward engine mount 

of Model 747–8 airplanes, which shares 

a similar design to the forward engine 

mount of Model 787–8 and 787–9 

airplanes. This proposed AD would 

require, for certain airplanes, 

replacement of the four barrel nuts of 

the forward engine mount on each 

engine. For certain other airplanes, this 

proposed AD would require an 

inspection to determine if any forward 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules 76879 

engine mount barrel nut having a 

certain part number is installed, and 

related investigative and corrective 

actions if necessary. We are proposing 

this AD to detect and correct cracking of 

the forward engine mount barrel nuts; 

such cracking could result in reduced 

load capacity of the forward engine 

mount and could result in separation of 

an engine from the airplane, and 

consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by January 25, 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: 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 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– 

6548. 

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– 

6548; 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 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: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

Seattle Aircraft Certification Office, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6487; 

fax: 425–917–6590; email: 

allen.rauschendorfer@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– 

2015–6548; Directorate Identifier 2015– 

NM–114–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 

We received a report indicating that 

during the replacement of the No. 2 

engine on a Model 747–8 airplane, an 

operator conducted a non-destructive 

test (NDT) inspection of the barrel nuts 

on the forward engine mount and found 

cracks on two of the four barrel nuts. 

The same operator also discovered one 

cracked barrel nut on the No. 1 engine 

of the same Model 747–8 airplane. 

Boeing did an NDT inspection on the 

barrel nuts of the No. 2 engine of a 

Model 747–8 flight test airplane and 

discovered two barrel nuts with cracks. 

Since these initial findings, two 

additional barrel nuts were found 

cracked on two additional Model 747– 

8 airplanes. 

The barrel nuts are located at the 

forward end of the strut box and are 

used to fasten the forward engine mount 

to the strut. A barrel nut with a crack 

on one side is still able to carry ultimate 

load. A crack on both sides of a barrel 

nut will cause complete failure of the 

barrel nut. Complete failure of two or 

more barrel nuts on the same forward 

engine mount reduces the load capacity 

of the forward engine mount and could 

result in separation of an engine from 

the airplane, and consequent loss of 

control of the airplane. 

Model 787–8 and 787–9 airplanes 

with General Electric engines have a 

similar forward engine mount bolt and 

barrel nut configuration to that on 

Model 747–8 series airplanes. Therefore, 

Model 787–8 and 787–9 airplanes are 

subject to the same unsafe condition 

revealed on Model 747–8 series 

airplanes. We issued AD 2013–24–12, 

Amendment 39–17686 (78 FR 71989, 

December 2, 2013), to address this 

unsafe condition on Model 747–8 series 

airplanes. 

Relevant Service Information Under 1 

CFR Part 51 

We reviewed Boeing Service Bulletin 

B787–81205–SB710026–00, Issue 001, 

dated June 10, 2015. The service 

information describes procedures for 

replacing the forward engine mount 

barrel nuts with new, improved barrel 

nuts; doing an inspection to determine 

if barrel nuts having a certain part 

number are installed on the forward 

engine mount; and doing related 

investigative and corrective actions. 

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 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2015–6548. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
76880 Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules 

Differences Between This Proposed AD 

and the Service Information 

The service specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as 

Required for Compliance (RC) in any 

service information identified 

previously have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

For service information that contains 

steps that are labeled as RC, the 

following provisions apply: (1) The 

steps labeled as RC, including substeps 

under an RC step and any figures 

identified in an RC step, must be done 

to comply with the AD, and an AMOC 

is required for any deviations to RC 

steps, including substeps and identified 

figures; and (2) steps not labeled as RC 

may be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an AMOC, provided the RC steps, 

including substeps and identified 

figures, can still be done as specified, 

and the airplane can be put back in an 

airworthy condition. 

Costs of Compliance 

We estimate that this proposed AD 

affects 36 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 

Replacement (2 engines).29 work-hours × $85 per hour = 

$2,465 for 2 engines.

$1,988 per engine × 2 engines = 

$3,976.

$6,441 $64,410 (10 airplanes). 

Inspection for part number using maintenance 

records (2 engines).

1 work-hour × $85 per hour = $85 

for 2 engines.

$0 ..................................................... 85 $2,210 (26 airplanes). 

We estimate the following costs to do 

any related investigative actions that 

would be required based on the results 

of the proposed inspection. We have no 

way of determining the number of 

aircraft that might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Inspection (2 engines) ................................. 9 work-hours × $85 per hour = $765 for 2 engines ...................... $0 $765 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition corrective 

actions specified in this proposed AD. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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. 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules 76881 

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): 

No. FAA–2015–6548; Directorate Identifier 

2015–NM–114–AD. 

(a) Comments Due Date 

We must receive comments by January 25, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8 and 787–9 airplanes, 

certificated in any category, equipped with 

General Electric GEnx–1B engines, as 

identified in Boeing Service Bulletin B787– 

81205–SB710026–00, Issue 001, dated June 

10, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in barrel nuts on a forward engine 

mount of Model 747–8 airplanes, which 

shares a similar design to the forward engine 

mount of Model 787–8 and 787–9 airplanes. 

We are issuing this AD to detect and correct 

cracking of the forward engine mount barrel 

nuts; such cracking could result in reduced 

load capacity of the forward engine mount, 

and could result in separation of an engine 

from the airplane, and consequent loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement Barrel Nuts 

For Group 1 airplanes as identified in 

Boeing Service Bulletin B787–81205– 

SB710026–00, Issue 001, dated June 10, 2015: 

Except as provided by paragraph (i)(1) of this 

AD, at the time specified in paragraph 5., 

‘‘Compliance,’’ of Boeing Service Bulletin 

B787–81205–SB710026–00, Issue 001, dated 

June 10, 2015, replace the existing forward 

engine mount barrel nuts on each engine, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin B787– 

81205–SB710026–00, Issue 001, dated June 

10, 2015. 

(h) Part Number Inspection for Installed 

Barrel Nuts 

For Group 2 airplanes as identified in 

Boeing Service Bulletin B787–81205– 

SB710026–00, Issue 001, dated June 10, 2015: 

Except as provided by paragraph (i)(1) of this 

AD, at the time specified in paragraph 5. 

‘‘Compliance,’’ of Boeing Service Bulletin 

B787–81205–SB710026–00, Issue 001, dated 

June 10, 2015, review the aircraft 

maintenance records to determine if the 

airplane engine has been removed, installed, 

or replaced, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin B787–81205–SB710026–00, 

Issue 001, dated June 10, 2015. If the 

maintenance records indicate that a barrel 

nut having part number SL4081C14SP1 is 

installed, or if the part number of an installed 

barrel nut cannot be determined, before 

further flight, do the related investigative and 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin B787–81205– 

SB710026–00, Issue 001, dated June 10, 2015. 

(i) Exception to Service information 

(1) Where Boeing Service Bulletin B787– 

81205–SB710026–00, Issue 001, dated June 

10, 2015, specifies a compliance time ‘‘after 

the Issue 001 date on this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Service Bulletin B787– 

81205–SB710026–00, Issue 001, dated June 

10, 2015, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) 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 (k)(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, 

modification, or alteration 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. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (i)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

(1) For more information about this AD, 

contact Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

Seattle Aircraft Certification Office, FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6487; fax: 425–917– 

6590; email: allen.rauschendorfer@faa.gov. 

(2) 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. 

Issued in Renton, Washington, on 

December 4, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–31218 Filed 12–10–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF DEFENSE 

Office of the Secretary 

32 CFR Part 75 

RIN 0790–AI82 

[Docket ID: DOD–2011–OS–0127] 

Exceptional Family Member Program 

(EFMP) 

AGENCY: Office of the Under Secretary of 

Defense for Personnel and Readiness, 

DoD. 

ACTION: Proposed rule. 

SUMMARY: This proposed rule 

establishes the Exceptional Family 

Member Program (EFMP) and provides 

guidance, assigns responsibilities, and 

prescribes procedures for identifying a 

family member with special needs, and 

coordinating travel at government 

expense for family members of active 

duty Service members who meet the 


jstallworth on DSK7TPTVN1PROD with PROPOSALS