58294 Federal Register / Vol. 79, No. 188 / Monday, September 29, 2014 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0108; Directorate 

Identifier 2011–NM–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain The Boeing Company Model 

767 airplanes. The NPRM proposed to 

supersede AD 2003–13–01, which 

currently requires an inspection to 

detect cracks and fractures of the 

outboard hinge fitting assemblies on the 

trailing edge of the inboard main flap, 

and follow-on and corrective actions if 

necessary. For certain airplanes, AD 

2003–13–01 also requires inspecting to 

determine if a tool runout option has 

been performed in the area. The NPRM 

proposed to reduce a certain compliance 

time and adds airplanes to the 

applicability. The NPRM also provided 

optional terminating action for certain 

inspections. The NPRM was prompted 

by reports of hinge assembly fractures 

found before certain required 

compliance times in AD 2003–13–01. 

This action revises the NPRM by 

reducing repetitive inspection intervals 

for certain airplanes and limiting the 

inspection area. We are proposing this 

supplemental NPRM (SNPRM) to 

prevent the inboard aft flap from 

separating from the wing and 

potentially striking the airplane, which 

could result in damage to the 

surrounding structure and potential 

personal injury. Since these actions 

impose an additional burden over that 

proposed in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these proposed changes. 

DATES: We must receive comments on 

this SNPRM by November 13, 2014. 

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. 

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–2012– 

0108; 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6577; fax: 

425–917–6590; email: berhane.alazar@

faa.gov. 

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–2012–0108; Directorate Identifier 

2011–NM–049–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 issued an NPRM to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 767–200, –300, and –300F, and 

–400ER series airplanes. The NPRM 

published in the Federal Register on 

February 9, 2012 (77 FR 6685). The 

NPRM proposed to supersede AD 2003– 

13–01, Amendment 39–13201 (68 FR 

37402, June 24, 2003). The NPRM 

proposed to continue to require an 

inspection to detect cracks and fractures 

of the outboard hinge fitting assemblies 

on the trailing edge of the inboard main 

flap, and follow-on and corrective 

actions if necessary; and, for certain 

airplanes, a one-time inspection to 

determine if a tool runout option has 

been performed in the area. The NPRM 

also reduced compliance times on 

certain airplanes (Model 767–400ER 

series airplanes), revised the 

applicability, and added an optional 

terminating action. 

Actions Since Previous NPRM (77 FR 

6685, February 9, 2012) Was Issued 

Since we issued the NPRM (77 FR 

6685, February 9, 2012), we have 

received reports of hinge assembly 

fractures found before the current 

inspection interval on Model 767–200, 

–300, and –300F series airplanes. 

Comments 

We gave the public the opportunity to 

comment on the NPRM (77 FR 6685, 

February 9, 2012). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Support for the NPRM (77 FR 6685, 

February 9, 2012) 

An anonymous commenter supported 

the NPRM (77 FR 6685, February 9, 

2012). 

Request To Revise Applicability 

American Airlines requested that we 

revise the applicability of the NPRM (77 

FR 6685, February 9, 2012) to identify 

specific flap serial numbers instead of 

airplane line numbers. The commenter 

stated that a flap removed from the 

hinge assembly could then be installed 

on a different airplane. 

We partially agree. We agree that the 

subject flaps are rotable parts that may 

be removed and reinstalled on different 


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Federal Register / Vol. 79, No. 188 / Monday, September 29, 2014 / Proposed Rules 58295 

airplanes after compliance with the AD. 

We have therefore added new paragraph 

(q) in this SNPRM (and redesignated 

subsequent paragraphs) to prohibit 

installation of an inboard main flap 

unless it has been inspected and 

repaired in accordance with the 

requirements of this SNPRM. But we do 

not agree to change the applicability as 

requested because this AD action 

applies to the airplane, not a 

component. 

Since the flight cycles on the flaps 

may not be tracked by some operators, 

we mandated a compliance time tied to 

the total flight cycles of the airplane. 

Operators may request approval of an 

alternative compliance time, however, if 

the actual accumulated flight cycles on 

reinstalled flaps are known. 

Request To Specify Additional 

Airplanes Subject to Repetitive 

Inspection Requirement 

Boeing noted that paragraph (n) of the 

NPRM (77 FR 6685, February 9, 2012) 

specifies repetitive detailed and/or eddy 

current inspections for Model 767– 

400ER series airplanes. Boeing 

requested that we revise paragraph (n) 

of the NPRM to add the following 

revised service information: Boeing 

Alert Service Bulletin 767–57A0076, 

Revision 3, dated April 4, 2012 (for 

Models 767–200, –300, and –300F 

airplanes); and Boeing Alert Service 

Bulletin 767–57A0079, Revision 2, 

dated March 23, 2012 (for Model 767– 

400ER series airplanes). Boeing noted 

that this revised service information 

improves crack detection by clarifying 

the HFEC inspection area, based on a 

recent finding of a crack located along 

the edge of the inspection area on a 

Model 767–300 series airplane. We infer 

that Boeing wants us to revise paragraph 

(n) of the NPRM to add Model 767–200, 

–300, and –300F series airplanes. 

In addition, paragraph (o) of the 

NPRM (77 FR 6685, February 9, 2012) 

specifies a new optional terminating 

action. Boeing requested that we revise 

that paragraph to include terminating 

action for Model 767–200, –300, and 

–300F series airplanes (in addition to 

Model 767–400ER series airplanes), and 

to refer to Boeing Alert Service Bulletins 

767–57A0076, Revision 3, dated April 4, 

2012; and 767–57A0079, Revision 2, 

dated March 23, 2012. 

Further, Boeing requested that we 

revise paragraph (p) of the NPRM (77 FR 

6685, February 9, 2012) to provide 

credit for previous actions done using 

Boeing Service Bulletin 767–57A0076, 

Revision 2, dated November 22, 2006; 

and Boeing Service Bulletin 767– 

57A0079, Revision 1, dated May 6, 

2010. 

We agree with the requests, for the 

reasons provided by the commenter. We 

have revised paragraphs (n) and (o) in 

this SNPRM to add the referenced 

airplanes and service information. For 

information on the procedures and 

compliance times, see Boeing Alert 

Service Bulletin 767–57A0076, Revision 

3, dated April 4, 2012; and 767– 

57A0079, Revision 2, dated March 23, 

2012; at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2012–0108. 

We also have revised paragraph (p) of 

this SNPRM to provide credit for Boeing 

Service Bulletin 767–57A0076, Revision 

2, dated November 22, 2006; and Boeing 

Service Bulletin 767–57A0079, Revision 

1, dated May 6, 2010. We have 

determined that accomplishment of the 

actions specified in this revised service 

information before the effective date of 

the AD would provide an adequate level 

of safety. 

Request for Approval of AMOCs 

Boeing, American Airlines, and UPS 

requested that AMOCs previously 

approved for paragraph (i) of AD 2003– 

13–01, Amendment 39–13201 (68 FR 

37402, June 24, 2003), be considered 

acceptable for compliance with the 

requirements of paragraphs (g), (h), and 

(i) of the NPRM (77 FR 6685, February 

9, 2012). 

We agree. We have determined that 

the referenced AMOCs would provide 

an adequate level of safety. We have 

included this provision in new 

paragraph (r)(4) of this SNPRM. 

FAA’s Determination 

We are proposing this SNPRM 

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. Certain changes 

described above expand the scope of the 

NPRM (77 FR 6685, February 9, 2012). 

As a result, we have determined that it 

is necessary to reopen the comment 

period to provide additional 

opportunity for the public to comment 

on this SNPRM. 

Proposed Requirements of This SNPRM 

This SNPRM would require 

accomplishing the actions specified in 

Boeing Alert Service Bulletin 767– 

57A0076, Revision 3, dated April 4, 

2012; and 767–57A0079, Revision 2, 

dated March 23, 2012. 

Costs of Compliance 

We estimate that this proposed AD 

affects 440 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 

Retained detailed inspections .................... 10 work-hours × $85 per hour = $850 per 

inspection cycle.

$0 $850 per inspection 

cycle.

$374,000 per inspection cycle. 

Retained detailed and eddy current inspections.13 work-hours × $85 per hour = $1,105 

per inspection cycle.

$0 $1,105 per inspection cycle.$486,200 per inspection cycle. 

We estimate the following costs to do 

any necessary replacements 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 replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 32 work-hours × $85 per hour = $2,720 ................................................... $45,400 $48,120 


tkelley on DSK3SPTVN1PROD with PROPOSALS
58296 Federal Register / Vol. 79, No. 188 / Monday, September 29, 2014 / Proposed Rules 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

The Boeing Company: Docket No. FAA– 

2012–0108; Directorate Identifier 2011– 

NM–049–AD. 

(a) Comments Due Date 

We must receive comments by November 

13, 2014. 

(b) Affected ADs 

This AD replaces AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003). 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model 767–200, –300, and –300F series 

airplanes, as specified in Boeing Service 

Bulletin 767–57A0076, Revision 3, dated 

April 4, 2012. 

(2) Model 767–400ER series airplanes, as 

specified in Boeing Alert Service Bulletin 

767–57A0079, Revision 2, dated March 23, 

2012. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of hinge 

assembly fractures found before certain 

required compliance times on certain 

airplanes subject to AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003). We are issuing this AD to prevent 

the inboard aft flap from separating from the 

wing and potentially striking the airplane, 

which could result in damage to the 

surrounding structure and potential personal 

injury. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection 

This paragraph restates the requirements of 

paragraph (a) of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003), with revised service information. 

Perform either a detailed inspection, or a 

detailed inspection plus an eddy current 

inspection, of the outboard hinge fitting 

assemblies on the trailing edge of the inboard 

main flap to detect cracks and fractures and 

evidence of a tool runout option, as 

applicable. For the purposes of this AD, a 

detailed inspection is defined as an intensive 

visual examination of a specific structural 

area, system, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at 

intensity deemed appropriate by the 

inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required. 

(1) For Model 767–200, –300, and –300F 

series airplanes identified in Boeing Service 

Bulletin 767–57A0076, Revision 1, dated 

March 29, 2001: Inspect before the airplane 

accumulates 2,700 total flight cycles, or 

within 90 days after July 29, 2003 (the 

effective date of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003)), whichever occurs later, in 

accordance with Boeing Service Bulletin 

767–57A0076, Revision 1, dated March 29, 

2001; or Boeing Service Bulletin 767– 

57A0076, Revision 3, dated April 4, 2012. As 

of the effective date of this AD, only Boeing 

Service Bulletin 767–57A0076, Revision 3, 

dated April 4, 2012, may be used for the 

inspection. 

(2) For Model 767–400ER series airplanes 

identified in Boeing Alert Service Bulletin 

767–57A0079, dated June 20, 2002: Inspect 

before the airplane accumulates 12,000 total 

flight cycles, except as required by paragraph 

(m) of this AD, in accordance with Boeing 

Alert Service Bulletin 767–57A0079, dated 

June 20, 2002; or Boeing Alert Service 

Bulletin 767–57A0079, Revision 1, dated 

May 6, 2010; or Boeing Alert Service Bulletin 

767–57A0079, Revision 2, dated March 23, 

2012. As of the effective date of this AD, only 

Boeing Alert Service Bulletin 767–57A0079, 

Revision 2, dated March 23, 2012, may be 

used for the inspection. 

(h) Retained Follow-On/Corrective Actions 

This paragraph restates the requirements of 

paragraph (b) of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003), with revised service information. 

Following the initial inspections required by 

paragraph (g) of this AD, perform applicable 

follow-on and corrective actions at the times 

specified in Figure 1 of Boeing Service 

Bulletin 767–57A0076, Revision 1, dated 

March 29, 2001 (for Model 767–200, –300, 

and –300F series airplanes); or Boeing Alert 

Service Bulletin 767–57A0079, dated June 

20, 2002 (for Model 767–400ER series 

airplanes); until the initial inspection 

required by paragraph (n) of this AD is 

accomplished and repeat thereafter at the 

applicable times specified in paragraph (n) of 

this AD. Do the follow-on and corrective 

actions (including repetitive inspections and 

replacement of the fittings with new fittings) 

in accordance with Part 1 or Part 2 of Boeing 

Service Bulletin 767–57A0076, Revision 1, 

dated March 29, 2001; or Boeing Service 

Bulletin 767–57A0076, Revision 3, dated 

April 4, 2012 (for Model 767–200, –300, and 

–300F series airplanes); or Boeing Alert 

Service Bulletin 767–57A0079, dated June 

20, 2002, or Boeing Alert Service Bulletin 

767–57A0079, Revision 2, dated March 23, 

2012 (for Model 767–400ER series airplanes); 

except as required by paragraph (i)(2) of this 

AD. For Model 767–200, –300, and –300F 

series airplanes: If the fitting has the tool 

runout, and no cracking or fracture is found 

during the inspection, this AD requires no 

further action for that hinge fitting. As of the 

effective date of this AD, for the actions 

required by this paragraph, only Boeing Alert 

Service Bulletin 767–57A0079, Revision 2, 

dated March 23, 2012, may be used for Model 

767–400ER series airplanes; and only Boeing 

Alert Service Bulletin 767–57A0076, 


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Revision 3, dated April 4, 2012, may be used 

for Model 767–200, –300, and –300F 

airplanes. 

(i) Retained Exceptions to Service Bulletin 

Procedures 

This paragraph restates the requirements of 

paragraph (c) of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003). The following exceptions specified 

in paragraphs (i)(1) and (i)(2) of this AD 

apply. 

(1) Where the terminating action in Part 3 

of Boeing Service Bulletin 767–57A0076, 

Revision 1, dated March 29, 2001; and 

Revision 3, dated April 4, 2012; and Boeing 

Alert Service Bulletin 767–57A0079, dated 

June 20, 2002; Revision 1, dated May 6, 2010; 

and Revision 2, dated March 23, 2012; as 

applicable; is specified as corrective action, 

this AD requires that the terminating action, 

if required, be accomplished before further 

flight. 

(2) Boeing Service Bulletin 767–57A0076, 

Revision 1, dated March 29, 2001; and 

Revision 3, dated April 4, 2012; specify to 

contact Boeing before the terminating action 

is done as corrective action for any cracking 

or fracture found on a Model 767–200, –300, 

or –300F series airplane with the tool runout. 

However, this AD requires that any such 

crack or fracture on those airplanes be 

repaired in accordance with Part 3 of Boeing 

Service Bulletin 767–57A0076, Revision 1, 

dated March 29, 2001; or Revision 3, dated 

April 4, 2012. This AD does not require a 

report. 

(j) Retained Optional Terminating Action 

This paragraph restates the provisions of 

paragraph (f) of AD 2003–13–01, Amendment 

39–13201 (68 FR 37402, June 24, 2003), with 

revised service information. Unless required 

to do so by paragraph (h) of this AD, 

operators may choose to accomplish the 

terminating action (including replacement of 

the fittings with new fittings, and 

reinstallation of existing upper skin access 

panels and fairing midsections on the trailing 

edge of the main flap) in accordance with 

Part 3 of the Work Instructions of Boeing 

Service Bulletin 767–57A0076, Revision 1, 

dated March 29, 2001; or Boeing Alert 

Service Bulletin 767–57A0079, dated June 

20, 2002; as applicable; or do the terminating 

actions specified in paragraph (o) of this AD. 

As of the effective date of this AD, use only 

the terminating action specified in paragraph 

(o) of this AD. Accomplishment of the 

terminating action terminates the repetitive 

inspection requirements of paragraph (h) of 

this AD. 

(k) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install on any airplane identified 

in paragraph (c) of this AD, a hinge fitting 

assembly that has P/N 113T2271–13, 

113T2271–14, 113T2271–23, 113T2271–24, 

113T2271–29, 113T2271–30, 113T2271–33, 

113T2271–34, 113T2271–401, or 113T2271– 

402, unless the applicable requirements of 

this AD have been accomplished for that 

fitting. 

(l) Retained Credit for Previous Actions 

This paragraph restates the provisions of 

paragraph (g) of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003), with revised service information. 

Actions done before July 29, 2003 (the 

effective date of AD 2003–13–01), in 

accordance with Boeing Alert Service 

Bulletin 767–57A0076, dated October 26, 

2000, are acceptable for compliance with the 

corresponding requirements of paragraphs 

(g)(1), (h), and (j) of this AD. Boeing Alert 

Service Bulletin 767–57A0076, dated October 

26, 2000 is not incorporated by reference in 

this AD. 

(m) New Initial Inspection 

For Model 767–400ER airplanes identified 

in Boeing Alert Service Bulletin 767– 

57A0079, Revision 2, dated March 23, 2012, 

on which the inspection required in 

paragraph (g) of this AD has not been done 

as of the effective date of this AD: Before the 

accumulation of 6,000 total flight cycles, or 

within 750 flight cycles after the effective 

date of this AD, whichever occurs later, 

perform either a detailed inspection or a 

detailed inspection plus an eddy current 

inspection to detect cracks or fractures of the 

outboard hinge fitting assemblies on the 

trailing edge of the inboard main flap, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–57A0079, Revision 2, dated March 23, 

2012 Accomplishment of this inspection 

terminates the inspection requirement of 

paragraph (g)(2) of this AD. If any cracking 

or fracture is found, before further flight, 

replace the fittings in accordance with Part 

3 of the Work Instructions of Boeing Alert 

Service Bulletin 767–57A0079, Revision 2, 

dated March 23, 2012. 

(n) New Repetitive Inspections 

Repeat either inspection specified in 

paragraph (h) or (m) of this AD, as applicable, 

at intervals not to exceed the time specified 

in paragraph (n)(1) or (n)(2) of this AD, as 

applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–57A0076, Revision 3, 

dated April 4, 2012 (for Model 767–200, 

–300, and –300F series airplanes); or Boeing 

Alert Service Bulletin 767–57A0079, 

Revision 2, dated March 23, 2012 (for Model 

767–400ER series airplanes); until the actions 

specified in paragraph (o) of this AD are 

done. 

(1) If the most recent inspection was a 

detailed inspection: Do the next inspection 

within 300 flight cycles after doing the 

detailed inspection, and continue to repeat 

the inspection(s) thereafter at the time 

specified in paragraph (n) of this AD. 

(2) If the most recent inspections were a 

detailed inspection and an eddy current 

inspection: Do the next inspections at the 

applicable time specified in paragraph 

(n)(2)(i) or (n)(2)(ii) of this AD, and continue 

to repeat the inspection(s) thereafter at the 

time specified in paragraph (n) of this AD. 

(i) For Model 767–200, –300, and –300F 

series airplanes: Do the next inspection at the 

applicable time specified in paragraph 

(n)(2)(i)(A) or (n)(2)(i)(B) of this AD. 

(A) If the detailed inspection and eddy 

current inspection were done before the 

effective date of this AD: Do the next 

inspection within 1,500 flight cycles after 

doing the detailed and eddy current 

inspections. 

(B) If the detailed inspection and eddy 

current inspection were done on or after the 

effective date of this AD: Do the next 

inspection within 750 flight cycles after 

doing the detailed and eddy current 

inspection. 

(ii) For Model 767–400ER series airplanes: 

Do the next inspection within 750 flight 

cycles after doing the detailed inspection and 

eddy current inspection. 

(o) New Optional Terminating Action 

Replacement of the fittings in accordance 

with Part 3 of the Work Instructions of 

Boeing Alert Service Bulletin 767–57A0079, 

Revision 2, dated March 23, 2012 (for Model 

767–400ER series airplanes); or Part 3 of the 

Work Instructions of Boeing Alert Service 

Bulletin 767–57A0076, Revision 3, dated 

April 4, 2012 (for Model 767–200, –300, and 

–300F series airplanes); terminates the 

repetitive inspections required by paragraphs 

(h) and (n) of this AD. 

(p) Credit for Previous Actions 

(1) Actions done before the effective date 

of this AD in accordance with the service 

information identified in paragraph (p)(1)(i) 

or (p)(1)(ii) of this AD are acceptable for 

compliance with the corresponding 

requirements of paragraphs (h), (n), and (o) 

of this AD. 

(i) Boeing Alert Service Bulletin 767– 

57A0076, Revision 1, dated March 29, 2001, 

which is incorporated by reference in AD 

2003–13–01, Amendment 39–13201 (68 FR 

37402, June 24, 2003); or Boeing Alert 

Service Bulletin 767–57A0076, Revision 2, 

dated November 22, 2006, which is not 

incorporated by reference in this AD. 

(ii) Boeing Alert Service Bulletin 767– 

57A0079, dated June 20, 2002, which is 

incorporated by reference in AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003); and Boeing Alert Service Bulletin 

767–57A0079, Revision 1, dated May 6, 2010, 

which is not incorporated by reference in this 

AD. 

(2) Actions done before the effective date 

of this AD in accordance with the service 

information identified in paragraph (p)(2)(i) 

or (p)(2)(ii) of this AD are acceptable for 

compliance with the corresponding 

requirements of paragraph (j) of this AD. 

(i) Boeing Alert Service Bulletin 767– 

57A0076, Revision 2, dated November 22, 

2006, which is not incorporated by reference 

in this AD. 

(ii) Boeing Alert Service Bulletin 767– 

57A0079, Revision 1, dated May 6, 2010, 

which is not incorporated by reference in this 

AD. 

(q) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install an inboard main flap on 

any airplane, unless the flap has been 

inspected and all applicable corrective 

actions have been performed in accordance 

with the requirements of this AD. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
58298 Federal Register / Vol. 79, No. 188 / Monday, September 29, 2014 / Proposed Rules 

(r) 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 (s)(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. 

(4) AMOCs approved previously in 

accordance with AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003), are approved as AMOCs for the 

corresponding provisions of paragraphs (g), 

(h), and (i) of this AD. 

(s) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

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

email: berhane.alazar@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 copies of the 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 

September 19, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–23138 Filed 9–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 165 

[Docket Number USCG–2013–1009] 

RIN 1625–AA87 

Security Zones; Dignitary Arrival/

Departure and United Nations 

Meetings, New York, NY 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of Proposed Rulemaking. 

SUMMARY: The Coast Guard proposes to 

amend 33 CFR 165.164 by establishing 

three security zones to replace the three 

regulated navigation areas (RNAs) 

currently contained within this section. 

The Coast Guard also proposes to 

disestablish these three RNAs. The three 

proposed security zones, just like the 

RNAs they replace, are meant to 

promote public safety and to protect 

dignitaries who visit the United Nations 

in New York, NY. 

DATES: Comments and related material 

must be received by the Coast Guard on 

or before October 29, 2014. 

Requests for public meetings must be 

received by the Coast Guard on or before 

October 6, 2014. 

ADDRESSES: You may submit comments 

identified by docket number using any 

one of the following methods: 

(1) Federal eRulemaking Portal: 

http://www.regulations.gov. 

(2) Fax: 202–493–2251. 

(3) Mail or Delivery: Docket 

Management Facility (M–30), U.S. 

Department of Transportation, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC 20590–0001. Deliveries 

accepted between 9 a.m. and 5 p.m., 

Monday through Friday, except federal 

holidays. The telephone number is 202– 

366–9329. 

See the ‘‘Public Participation and 

Request for Comments’’ portion of the 

SUPPLEMENTARY INFORMATION section 

below for further instructions on 

submitting comments. To avoid 

duplication, please use only one of 

these three methods. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this rule, call or 

email Mr. Jeff Yunker, Coast Guard 

Sector New York, Waterways 

Management Division; telephone (718) 

354–4195, email Jeff.M.Yunker@

uscg.mil or Lieutenant Myles Greenway, 

Coast Guard First District Waterways 

Management Branch, telephone (617) 

223–8385, email Myles.J.Greenway@

uscg.mil. If you have questions on 

viewing or submitting material to the 

docket, call Cheryl Collins, Program 

Manager, Docket Operations, telephone 

(202) 366–9826. 

SUPPLEMENTARY INFORMATION: 

Table of Acronyms 

DHS Department of Homeland Security 

FR Federal Register 

MOA Memorandum of Agreement 

NPRM Notice of Proposed Rulemaking 

RNA Regulated Navigation Area 

SNPRM Supplemental Notice of Proposed 

Rulemaking 

UN United Nations 

UNGA United Nations General Assembly 

USSS United States Secret Service 

A. Public Participation and Request for 

Comments 

We encourage you to participate in 

this rulemaking by submitting 

comments and related materials. All 

comments received will be posted 

without change to http://

www.regulations.gov and will include 

any personal information you have 

provided. 

1. Submitting Comments 

If you submit a comment, please 

include the docket number for this 

rulemaking, indicate the specific section 

of this document to which each 

comment applies, and provide a reason 

for each suggestion or recommendation. 

You may submit your comments and 

material online at http://

www.regulations.gov, or by fax, mail, or 

hand delivery, but please use only one 

of these means. If you submit a 

comment online, it will be considered 

received by the Coast Guard when you 

successfully transmit the comment. If 

you fax, hand deliver, or mail your 

comment, it will be considered as 

having been received by the Coast 

Guard when it is received at the Docket 

Management Facility. We recommend 

that you include your name and a 

mailing address, an email address, or a 

telephone number in the body of your 

document so that we can contact you if 

we have questions regarding your 

submission. 

To submit your comment online, go to 

http://www.regulations.gov, type the 

docket number [USCG–2013–1009] in 

the ‘‘SEARCH’’ box and click 

‘‘SEARCH.’’ Click on ‘‘Submit a 

Comment’’ on the line associated with 

this rulemaking. 

If you submit your comments by mail 

or hand delivery, submit them in an 

unbound format, no larger than 81⁄2 by 

11 inches, suitable for copying and 

electronic filing. If you submit 

comments by mail and would like to 

know that they reached the Facility, 

please enclose a stamped, self-addressed 


tkelley on DSK3SPTVN1PROD with PROPOSALS