74052 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 

(u) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (v)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-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) AMOCs approved for AD 2009–02–06, 

Amendment 39–15796 (74 FR 10469, March 

11, 2009); AD 2009–02–06 R1, Amendment 

39–16015 (74 FR 45979, September 6, 2009); 

and AD 2011–23–05, Amendment 39–16856 

(76 FR 67343, November 1, 2011); are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(v) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6447; fax: 425– 

917–6590; email: wayne.lockett@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, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on 

November 17, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30008 Filed 11–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5816; Directorate 

Identifier 2015–NM–029–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 supersede 

Airworthiness Directive (AD) 2006–10– 

16, which applies to all The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, 747SR, and 747SP 

series airplanes. AD 2006–10–16 

requires, for certain airplanes, repetitive 

inspections for cracking of the outboard 

and center sections of the horizontal 

stabilizer, and repair if necessary. For 

certain other airplanes, AD 2006–10–16 

requires a detailed inspection to 

determine the type of fasteners, and 

related investigative actions and repair 

if necessary. Since we issued AD 2006– 

10–16, additional cracking was found in 

the splice plates, hinge fittings, terminal 

fittings, the upper skin of the outboard 

and center sections, and the rear spar 

webs before reaching the inspection 

interval specified in AD 2006–10–16. 

Cracked and fractured Maraging steel 

fasteners were also found. This 

proposed AD would reduce the 

compliance time for certain inspections 

and would add repetitive inspections 

for cracking of the splice plates, hinge 

fittings, terminal fittings, the upper skin 

of the outboard and center sections, and 

the rear spar webs in Zone B. This 

proposed AD would also add an 

inspection to determine whether 

fasteners are magnetic in Zone C, 

repetitive ultrasonic inspections for 

cracking and fractures of affected 

fasteners, and related investigative and 

corrective actions if necessary. This 

proposed AD would also add an 

optional modification, which would 

terminate certain repetitive inspections, 

and would add post-modification 

inspections and corrective action if 

necessary. We are proposing this AD to 

detect and correct this cracking, which 

could lead to reduced structural 

capability of the outboard and center 

sections of the horizontal stabilizer and 

could result in loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by January 11, 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– 

5816. 

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– 

5816; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74053 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–5816; Directorate Identifier 

2015–NM–029–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 

On May 8, 2006, we issued AD 2006– 

10–16, Amendment 39–14600 (71 FR 

28570, May 17, 2006), for all The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, 747SR, and 747SP 

series airplanes. AD 2006–10–16 

requires, for certain airplanes, repetitive 

inspections for cracking of the outboard 

and center sections of the horizontal 

stabilizer, and repair if necessary. For 

certain other airplanes, AD 2006–10–16 

requires a detailed inspection to 

determine the type of fasteners, related 

investigative actions, and repair if 

necessary. AD 2006–10–16 resulted 

from reports of cracking in the outboard 

and center section of the aft upper skin 

of the horizontal stabilizer, the rear spar 

chord, rear spar web, terminal fittings, 

and splice plates; and a report of 

fractured and cracked steel fasteners. 

We issued AD 2006–10–16 to detect and 

correct this cracking, which could lead 

to reduced structural capability of the 

outboard and center sections of the 

horizontal stabilizer and could result in 

loss of control of the airplane. 

Actions Since AD 2006–10–16, 

Amendment 39–14600 (71 FR 28570, 

May 17, 2006), Was Issued 

Since we issued AD 2006–10–16, 

Amendment 39–14600 (71 FR 28570, 

May 17, 2006), additional cracking was 

found in the splice plates, hinge fittings, 

terminal fittings, the upper skin of the 

outboard and center sections, and the 

rear spar webs before reaching the 

inspection interval specified in AD 

2006–10–16. Cracked and fractured 

Maraging steel fasteners were also 

found. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Service Bulletin 

747–55A2050, Revision 2, dated January 

23, 2015. The service information 

describes procedures for accomplishing 

Zone A, Zone B, and Zone C inspections 

for cracking of the upper skin and upper 

rear spar chord of the outboard and 

center sections of the horizontal 

stabilizer, and related investigative and 

corrective actions if necessary. The 

service information also describes 

procedures for a magnetic inspection to 

determine the type of fasteners, 

ultrasonic inspections for cracking and 

fractures of affected fasteners, and 

related investigative actions and 

corrective actions if necessary. The 

service information also describes 

procedures for an optional modification, 

which would end certain repetitive 

inspections, and procedures for postmodification inspections and corrective 

action if necessary. 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 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2006–10–16, Amendment 39–14600 (71 

FR 28570, May 17, 2006), this proposed 

AD would retain all of the requirements. 

Those requirements are referenced in 

the service information identified 

previously, which, in turn, is referenced 

in paragraph (g) of this proposed AD. 

This proposed AD would reduce the 

compliance time for certain inspections 

and add new repetitive inspections for 

cracking of the splice plates, hinge 

fittings, terminal fittings, the upper skin 

of the outboard and center sections, and 

the rear spar webs in Zone B. This 

proposed AD would also add an 

inspection to determine whether 

fasteners are magnetic in Zone C (made 

of H–11 steel), repetitive ultrasonic 

inspections for cracking and fractures of 

affected fasteners, and related 

investigative and corrective actions if 

necessary. This proposed AD would 

also add an optional modification, 

which would end certain repetitive 

inspections, and procedures for postmodification inspections and corrective 

action if necessary. This proposed AD 

also adds optional open-hole NDT 

inspections (high frequency eddy 

current inspections) for certain 

airplanes, for Zone B inspections. This 

proposed AD would also require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Difference Between this Proposed AD 

and the Service Bulletin.’’ For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

5816. 

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 action, 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. 

Difference Between This Proposed AD 

and the Service Bulletin 

Although Boeing Service Bulletin 

747–55A2050, Revision 2, dated January 

23, 2015, specifies that operators may 

contact the manufacturer for disposition 

of certain repair conditions, 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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 116 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

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74054 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 

ESTIMATED COSTS—REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Zone A Inspections (required by AD 2006– 

10–16, Amendment 39–14600).

8 work-hours × $85 per hour 

= $680.

$0 $680 Up to $78,880. 

Zone B Open-hole NDT Inspection (required 

by AD 2006–10–16, Amendment 39–14600 

for Groups 3, 4, and 5 airplanes; and for 

Groups 1, 2, and 3 airplanes, if done).

30 work-hours × 85 per hour 

= 2,550.

0 2,550 Up to $295,800. 

Zone C Maraging or H–11 Steel Fastener Inspection (required by AD 2006–10–16, 

Amendment 39–14600 for Groups 1, 2, 

and 3 airplanes).

8 work-hours × 85 per hour = 

680.

0 680 Up to $78,880. 

New Zone B proposed inspections ................ 248 work-hours × 85 per hour 

= 21,080.

0 21,080 $2,445,280. 

New Zone C proposed inspection .................. 26 work-hours × 85 per hour 

= 2,210.

0 2,210 $256,360. 

ESTIMATED COSTS—OPTIONAL ACTIONS

Action Labor cost Parts cost Cost per product 

Open-hole NDT inspections (high 

frequency eddy current inspections.

Up to 298 work-hours × $85 per 

hour = up to $25,330.

$$0 ................................................ Up to $25,330. 

Zone B Modification ....................... Up to 313 work-hours × $85 per 

hour = up to $26,605.

Up to $3,486 ................................. Up to $30,091. 

Post-Modification Inspections ........ Up to 298 work-hours × $85 per 

hour = up to $25,330.

$0 .................................................. Up to $25,330. 

We have received no definitive data 

that would enable us to provide a cost 

estimate 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 have 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 that the 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 

removing Airworthiness Directive AD 

2006–10–16, Amendment 39–14600 (71 

FR 28570, May 17, 2006), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2015–5816; Directorate Identifier 2015– 

NM–029–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by January 11, 2016. 

(b) Affected ADs 

This AD replaces AD 2006–10–16, 

Amendment 39–14600 (71 FR 28570, May 17, 

2006). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747–400F, 

747SR, and 747SP series airplanes; 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking found in the splice plates, hinge 

fittings, terminal fittings, the upper skin of 

the outboard and center sections, and the rear 

spar webs before reaching the inspection 

interval specified in AD 2006–10–16. 

Cracked and fractured Maraging steel 

fasteners were also found. We are issuing this 

AD to detect and correct this cracking, which 

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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74055 

could lead to reduced structural capability of 

the outboard and center sections of the 

horizontal stabilizer and could result in loss 

of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections/Investigative and 

Corrective Actions 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, except as required by 

paragraphs (h)(1) and (h)(2) of this AD: Do 

the applicable actions specified in 

paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of 

this AD, and all applicable related 

investigative and corrective actions, in 

accordance with the applicable part of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, except as required by 

paragraph (h)(3) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. Repeat the applicable 

inspections specified in paragraphs (g)(1), 

(g)(2), (g)(3), and (g)(4) of this AD at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–55A2050, Revision 2, dated January 23, 

2015. 

(1) For Group 1 through 3 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015: 

Do non-destructive test (NDT) inspections 

(ultrasonic, high frequency eddy current, and 

low frequency eddy current inspections) or 

open-hole NDT inspections (high frequency 

eddy current inspections), of Zone B for 

cracking in accordance with Part 3 or Part 4 

of the Accomplishment Instructions of 

Boeing Service Bulletin 747–55A2050, 

Revision 2, dated January 23, 2015, as 

applicable. 

(2) For Group 4 through 6 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015: 

Do open-hole NDT inspections (high 

frequency eddy current inspections), of Zone 

B for cracking in accordance with Part 4 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015. 

(3) For Group 7 through 9 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015: 

Do inspections of Zone A (detailed or high 

frequency eddy current inspections) and 

Zone B (high frequency eddy current 

inspections) for cracking, in accordance with 

Part 1, Part 2, or Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, as applicable. 

(4) For Group 1 through 3 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015: 

Do an inspection of Zone C Maraging or H– 

11 steel fasteners to determine whether 

fasteners are magnetic, in accordance with 

Part 6 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–55A2050, 

Revision 2, dated January 23, 2015. 

(h) Exceptions to Service Bulletin 

Specifications 

(1) Where Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015, 

specifies a compliance time ‘‘after the 

Revision 2 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) The Condition column of Table 1 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, refers to ‘‘airplanes 

with certain total flight cycles and total flight 

hours.’’ This AD, however, applies to the 

airplanes with the specified total flight cycles 

and total flight hours as of the effective date 

of this AD. 

(3) Where Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015, 

specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(i) Optional Terminating Action 

(1) For Group 1 through 3 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015: 

Accomplishing the Zone B modification, 

including all applicable related investigative 

and corrective actions, specified in Part 7 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, except as required by 

paragraph (h)(3) of this AD, terminates the 

repetitive inspections specified in paragraphs 

(i)(1)(i) and (i)(1)(ii) of this AD for the 

modified area only. 

(i) Inspections required by paragraph (g)(1) 

of this AD for Zone B, as specified in Part 

3 and Part 4 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015. 

(ii) Inspections required by paragraph (g)(4) 

of this AD for Zone C, as specified in Part 

5 and Part 6 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015. 

(2) For Group 1 through 3 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015: 

Accomplishing the Zone B open hole NDT 

inspection, repairing any cracking as 

applicable, and replacing fasteners as 

specified in Part 4 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015, 

terminates the repetitive ultrasonic 

inspections required by paragraph (g)(4) of 

this AD for Zone C, as specified in Part 6 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, for the inspected area 

only. 

(3) For Group 4 through 9 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015: 

Accomplishing the Zone B modification, 

including all applicable related investigative 

and corrective actions, specified in Part 7 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, except as required by 

paragraph (h)(3) of this AD, terminates the 

repetitive inspections required by paragraph 

(g)(2) or (g)(3) of this AD, as applicable, only 

for Zone B, as specified in Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, for the modified area 

only. 

(j) Repetitive Post-Modification Inspections 

and Corrective Actions 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015: Do the applicable 

inspections specified in paragraphs (j)(1) and 

(j)(2) of this AD and all applicable corrective 

actions, in accordance with Part 8 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–55A2050, Revision 2, 

dated January 23, 2015, except as required by 

paragraph (h)(3) of this AD. Do all applicable 

corrective actions before further flight. 

Repeat the applicable inspections at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–55A2050, Revision 2, dated January 23, 

2015. 

(1) For Group 1 through 3 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015 

on which the Zone B modification specified 

in paragraph (i)(1) of this AD is done: Do 

non-destructive test (NDT) inspections 

(ultrasonic, high frequency eddy current, and 

low frequency eddy current inspections) or 

open-hole NDT inspections (high frequency 

eddy current inspections) of Zone B for 

cracking. 

(2) For Group 4 through 9 airplanes 

identified in Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015 

on which the Zone B modification specified 

in paragraph (i)(3) of this AD is done: Do 

open-hole NDT inspections (high frequency 

eddy current inspections) of Zone B for 

cracking. 

(k) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install any Maraging or H–11 

steel fasteners in the locations specified in 

this AD. Where Boeing Service Bulletin 747– 

55A2050, Revision 2, dated January 23, 2015, 

specifies to install H–11 bolts (kept 

fasteners), this AD requires installation of 

Inconel bolts. 

(l) 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 (m)(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. 

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74056 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 

(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. 

(4) AMOCs approved for AD 2006–10–16, 

Amendment 39–14600 (71 FR 28570, May 17, 

2006), are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD, except for approved AMOCs that 

allow installation of Maraging or H–11 steel 

fasteners. 

(m) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6428; fax: 425–917–6590; email: 

nathan.p.weigand@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 

November 19, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–30120 Filed 11–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5813; Directorate 

Identifier 2014–NM–111–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation 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 

Dassault Aviation Model FALCON 7X 

airplanes. This proposed AD was 

prompted by a fuel leak that occurred in 

the baggage compartment during fuel 

system pressurization. This proposed 

AD would require opening the fuel 

boxes and restoring the sealing. We are 

proposing this AD to detect and correct 

failure of a connector or coupling on a 

fuel line, which, in combination with a 

leak in the corresponding enclosure 

(i.e., fuel box), could result in a fire in 

the baggage compartment and affect the 

safe flight of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 11, 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Dassault 

Falcon Jet, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http://

www.dassaultfalcon.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. 

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– 

5813; 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 Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1137; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–5813; Directorate Identifier 

2014–NM–111–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 based on 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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0116, dated May 13, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Dassault 

Aviation Model FALCON 7X airplanes. 

The MCAI states: 

During the fuel system pressurization of a 

production line Falcon 7X aeroplane, a fuel 

leak occurred in the baggage compartment. 

The technical investigations concluded that a 

double failure of a connector (or coupling) on 

a fuel line, in combination with a defective 

fuel tightness of the corresponding enclosure 

(fuel box), caused the leak. 

Failure of the second barrier (fuel box) is 

a dormant failure, as this will only manifest 

itself in case of connector (or fuel pipe 

coupling) failure in flight. 

This condition, if not corrected, could 

result in a fire in the baggage compartment, 

which would affect the aeroplane safe flight. 

To address this potential unsafe condition, 

Dassault Aviation issued Service Bulletin 

(SB) F7X–284, which provides instructions to 

restore the sealing of the Left Hand (LH) and 

Right Hand (RH) fuel boxes. 

For the reasons described above, this 

[EASA] AD requires opening of the fuel 

boxes and restoration of the sealing of the 

fuel boxes to meet the initial design 

specifications. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

5813. 

Related Service Information Under 1 

CFR Part 51 

Dassault Aviation has issued Service 

Bulletin 7X–284, Revision 1, dated 

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