Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 61093 

(f) Definition 

For the purpose of this AD, next piece-part 

exposure is when the nose cone assembly is 

removed from the engine. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any engine propeller shaft coupling, 

P/N 3107065–1, 865888–3, 865888–6, or 

865888–8, into any engine. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712– 

4137; phone: 562–627–5246; fax: 562–627– 

5210; email: joseph.costa@faa.gov. 

(2) Allied-Signal Aerospace Company 

Service Bulletin No. TPE331–72–0873, 

Revision 1, dated May 20, 1993 and 

Honeywell International Inc. Operating 

Information Letter OI331–26, dated March 2, 

2010, which are not incorporated by 

reference in this AD, can be obtained from 

Honeywell International, using the contact 

information in paragraph (i)(3) of this AD. 

(3) For service information identified in 

this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034– 

2802; phone: 800–601–3099; Internet: http:// 

portal.honeywell.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on: 

October 2, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–25606 Filed 10–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0108; Directorate 

Identifier 2011–NM–049–AD; Amendment 

39–18215; AD 2015–15–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2003–13– 

01 for certain The Boeing Company 

Model 767 airplanes. AD 2003–13–01 

required 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 

required an inspection to determine if a 

tool runout option has been performed 

in the area. This new AD reduces 

certain compliance times, adds 

airplanes to the applicability, and 

provides optional terminating action for 

certain inspections. This AD was 

prompted by reports of hinge assembly 

fractures found before certain required 

compliance times in AD 2003–13–01. 

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. 

DATES: This AD is effective November 

13, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 13, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 29, 2003 (68 FR 

37402, June 24, 2003). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2012– 

0108. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.govby 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, 


rmajette on DSK7SPTVN1PROD with RULESER09OC15.000</GPH>
61094 Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6447; 

fax: 425–917–6590; email: 

wayne.lockett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to supersede AD 

2003–13–01, Amendment 39–13201 (68 

FR 37402, June 24, 2003). AD 2003–13– 

01 applied to certain The Boeing 

Company Model 767 airplanes. The 

SNPRM published in the Federal 

Register on September 29, 2014 (79 FR 

58294). We preceded the SNPRM with 

a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on February 9, 2012 (77 FR 

6685). 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. For 

certain airplanes, the NPRM proposed to 

continue to require inspecting to 

determine if a tool runout option has 

been performed in the area. The NPRM 

also proposed to reduce a certain 

compliance time and add airplanes to 

the applicability. The NPRM 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. 

The SNPRM revised the NPRM by 

reducing repetitive inspection intervals 

for certain airplanes and limiting the 

inspection area. 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the SNPRM (79 FR 58294, 

September 29, 2014) and the FAA’s 

response to each comment. 

Support for the SNPRM (79 FR 58294, 

September 29, 2014) 

Boeing concurred with the contents of 

the SNPRM (79 FR 58294, September 

29, 2014). 

Requests To Remove Certain Provisions 

for Spare Parts 

American Airlines and UPS requested 

that we revise the SNPRM (79 FR 58294, 

September 29, 2014) by removing 

paragraph (q), because its provisions are 

redundant with the requirements of 

paragraph (k) of the SNPRM. 

We agree with the requests, for the 

reason provided by the commenters. We 

have removed the referenced paragraph 

and redesignated subsequent paragraphs 

accordingly. 

Request To Clarify Replacement 

Requirements 

American Airlines requested that we 

revise the SNPRM (79 FR 58294, 

September 29, 2014) to identify the part 

numbers for fittings that are acceptable 

for terminating action, but to not require 

specific removal and reinstallation 

procedures. The commenter added that 

the design change of the fitting—not the 

installation method—corrects the unsafe 

condition. 

We partially agree with the request. 

Although we did not identify the part 

numbers, we revised paragraph (o) in 

this AD to specify only the specific step 

that provides the replacement 

instructions and identifies the part 

number of the new fittings. Other 

removal and reinstallation actions 

related to the fitting replacement may be 

done using accepted methods in 

accordance with the operator’s 

maintenance or inspection program. 

We disagree with American Airlines’ 

assertion that only the fitting design 

‘‘corrects the unsafe condition.’’ ADs 

contain requirements that are related to 

addressing the unsafe condition, as 

determined by the FAA and the design 

approval holder that developed the 

service information. Therefore, many 

provisions of ADs address aspects of 

accomplishing the required 

maintenance that are necessary to 

prevent operators from inadvertently 

aggravating the unsafe condition or 

introducing new unsafe conditions. As 

in this case, the replacement 

instructions provided in the referenced 

service information are reasonably 

related to addressing the unsafe 

condition. 

As always, operators preferring to use 

a method other than that specified in 

the referenced service information may 

request approval for an alternative 

method of compliance and, if approved, 

may use it instead of the procedures 

specified in the service information. 

We further clarified this action 

throughout this AD by revising the 

description of the replacement part by 

specifying ‘‘the inboard main flap 

outboard hinge fittings.’’ 

Effect of Winglets on AD 

Aviation Partners Boeing, United 

Airlines, Delta Air Lines, and UPS 

requested that the SNPRM (79 FR 

58294, September 29, 2014) specify that 

accomplishment of supplemental type 

certificate (STC) ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

59027f43b9a7486e86257b1d006591ee/

$FILE/ST01920SE.pdf) does not affect 

the actions in the SNPRM. 

We concur with the request. We have 

redesignated the introductory text of 

paragraph (c) of the SNPRM (79 FR 

58294, September 29, 2014) as 

paragraph (c)(1), and subparagraphs 

(c)(1) and (c)(2) as (c)(1)(i) and (c)(1)(ii), 

and added new paragraph (c)(2) to this 

AD to state that installation of STC 

ST01920SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

59027f43b9a7486e86257b1d006591ee/

$FILE/ST01920SE.pdf) does not affect 

the ability to accomplish the actions 

required by this final rule. Therefore, for 

airplanes on which STC ST01920SE is 

installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. 

Change of Location for Certain Credit 

Service Information 

We have removed Boeing Alert 

Service Bulletin 767–57A0079, Revision 

1, dated May 6, 2010, which is referred 

to for credit for certain actions, from 

paragraph (g)(2) of the proposed AD. 

Instead, we have revised paragraph 

(p)(1) of this AD to specifically provide 

credit for actions required by paragraph 

(g)(2) of this AD, if those actions were 

performed before the effective date of 

this AD using Boeing Alert Service 

Bulletin 767–57A0079, Revision 1, 

dated May 6, 2010. We have 

redesignated subsequent paragraphs 

(including the addition of new 

paragraph (p)(3)) accordingly. This 

change does not affect the intent of 

paragraph (g)(2) of this AD. 


rmajette on DSK7SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 61095 

Change to Retained Credit for Previous 

Actions Language 

We have revised the wording in 

paragraph (l) of this AD; this change has 

not changed the intent of that 

paragraph. 

Change to Previous AMOCs Paragraph 

We have added a reference to 

paragraph (j) of this AD in paragraph 

(q)(4) of this AD to account for any 

AMOCs that might have been approved 

for the optional action specified in 

paragraph (j) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (79 FR 

58294, September 29, 2014) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (79 FR 58294, 

September 29, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 767–57A0079, Revision 2, 

dated March 23, 2012; and Boeing Alert 

Service Bulletin 767–57A0076, Revision 

3, dated April 4, 2012. The service 

information describes procedures for 

repetitive eddy current inspections for 

cracks or fractures of the outboard hinge 

fitting assemblies on the trailing edge of 

the inboard main flap. The service 

information also describes procedures 

for replacing the fittings, which would 

eliminate the need for the repetitive 

inspections. 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 final rule. 

Costs of Compliance 

We estimate that this AD affects 440 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

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 

inspection. We have no way of 

determining the number of airplanes 

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 

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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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) 

2003–13–01, Amendment 39–13201 (68 

FR 37402, June 24, 2003), and adding 

the following new AD: 


rmajette on DSK7SPTVN1PROD with RULES
61096 Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 

2015–15–06 The Boeing Company: 

Amendment 39–18215; Docket No. 

FAA–2012–0108; Directorate Identifier 

2011–NM–049–AD. 

(a) Effective Date 

This AD is effective November 13, 2015. 

(b) Affected ADs 

This AD replaces AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company airplanes, certificated in any 

category, identified in paragraphs (c)(1)(i) 

and (c)(1)(ii) of this AD. 

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

airplanes, as specified in Boeing Alert 

Service Bulletin 767–57A0076, Revision 3, 

dated April 4, 2012. 

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

specified in Boeing Alert Service Bulletin 

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

2012. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

59027f43b9a7486e86257b1d006591ee/$FILE/

ST01920SE.pdf) does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST01920SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(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 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, With Revised 

Service Information 

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 the Accomplishment Instructions of 

Boeing Alert 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 the Accomplishment 

Instructions of 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, 

With Revised Service Information 

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 Alert 

Service Bulletin 767–57A0079, dated June 

20, 2002; or in accordance with the 

Accomplishment Instructions of the service 

information identified in paragraph (h)(1) or 

(h)(2) of this AD; 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 the service information 

identified in paragraph (h)(1) or (h)(2) of this 

AD, as applicable, may be used. 

(1) Boeing Service Bulletin 767–57A0076, 

Revision 3, dated April 4, 2012 (for Model 

767–200, –300, and –300F series airplanes). 

(2) Boeing Alert Service Bulletin 767– 

57A0079, Revision 2, dated March 23, 2012 

(for Model 767–400ER series airplanes). 

(i) Retained Exceptions to Service Bulletin 

Procedures, Without the Reporting 

Requirement and With Revised Service 

Information 

This paragraph restates the requirements of 

paragraphs (c) and (d) of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003), without the reporting requirement 

and with revised service information. 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, 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 

Boeing Alert Service Bulletin 767–57A0076, 

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 the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–57A0076, 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). 

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 


rmajette on DSK7SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 61097 

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

assembly that has part number (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, 

With Revised Credit Provisions 

This paragraph restates the provisions of 

paragraph (g) of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003), with revised credit provisions. 

This paragraph provides credit for actions 

required by paragraphs (g)(1), (h), and (j) of 

this AD, if those actions were performed 

before July 29, 2003 (the effective date of AD 

2003–13–01), using Boeing Alert Service 

Bulletin 767–57A0076, dated October 26, 

2000, which 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 the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–57A0079, Revision 2, 

dated March 23, 2012. 

(n) New Repetitive Inspections 

Repeat the 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 inboard main flap 

outboard hinge fittings in accordance with 

step 4 of Part 3 of the Work Instructions of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 767–57A0079, 

Revision 2, dated March 23, 2012 (for Model 

767–400ER series airplanes); or step 4 of Part 

3 of the Work Instructions of 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); terminates 

the repetitive inspections required by 

paragraphs (h) and (n) of this AD. 

(p) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 767–57A0079, 

Revision 1, dated May 6, 2010, which is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraphs (h), (n), and 

(o) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information identified in 

paragraph (p)(2)(i), (p)(2)(ii), (p)(2)(iii), or 

(p)(2)(iv) of this AD. 

(i) Boeing Alert Service Bulletin 767– 

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

which was incorporated by reference in AD 

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

37402, June 24, 2003), and continues to be 

incorporated by reference in this AD. 

(ii) Boeing Alert Service Bulletin 767– 

57A0076, Revision 2, dated November 22, 

2006, which is not incorporated by reference 

in this AD. 

(iii) Boeing Alert Service Bulletin 767– 

57A0079, dated June 20, 2002, which was 

incorporated by reference in AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003), and continues to be incorporated 

by reference in this AD. 

(iv) Boeing Alert Service Bulletin 767– 

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

which is not incorporated by reference in this 

AD. 

(3) This paragraph provides credit for 

actions required by paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraph (p)(3)(i) 

or (p)(3)(ii) 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) 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 (r)(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), (i), and (j) of this AD. 

(r) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office ACO, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6447; fax: 425–917–6590; 

email: wayne.lockett@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on November 13, 2015. 

(i) Boeing Alert Service Bulletin 767– 

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


rmajette on DSK7SPTVN1PROD with RULES
61098 Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Rules and Regulations 

(ii) Boeing Alert Service Bulletin 767– 

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

(4) The following service information was 

approved for IBR on July 29, 2003 (68 FR 

37402, June 24, 2003). 

(i) Boeing Alert Service Bulletin 767– 

57A0079, dated June 20, 2002. 

(ii) Boeing Service Bulletin 767–57A0076, 

Revision 1, dated March 29, 2001. 

(5) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

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

Internet https://www.myboeingfleet.com. 

(6) You may view this service information 

at 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 30, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–25490 Filed 10–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1419; Directorate 

Identifier 2014–NM–183–AD; Amendment 

39–18279; AD 2015–20–01] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

188 series airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating the left and right lower 

surface panels of the wings are subject 

to widespread fatigue damage (WFD). 

This AD requires repetitive inspections 

for cracking at these panels, and repair 

if necessary. The AD also requires a onetime bolt-hole eddy current inspection 

of all open holes for cracking, repair if 

necessary, and modification. We are 

issuing this AD to prevent fatigue 

cracking of the left and right lower 

surface panels of the wings, which 

could result in reduced structural 

integrity of the airplane. 

DATES: This AD is effective November 

13, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 13, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, GA 

30063; telephone 770–494–5444; fax 

770–494–5445; email ams.portal@

lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. 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–2015–1419. 

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– 

1419; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Carl 

Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, GA 

30337; phone: 404–474–5554; fax: 404– 

474–5605; email: carl.w.gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Lockheed Martin 

Corporation/Lockheed Martin 

Aeronautics Company Model 188 series 

airplanes. The NPRM published in the 

Federal Register on June 5, 2015 (80 FR 

32069). The NPRM was prompted by an 

evaluation by the DAH indicating the 

left and right lower surface panels of the 

wings are subject to WFD. The NPRM 

proposed to require repetitive 

inspections for cracking at these panels, 

and repair if necessary. The NPRM also 

proposed to require a one-time bolt-hole 

eddy current inspection of all open 

holes for cracking, repair if necessary, 

and modification. We are issuing this 

AD to prevent fatigue cracking of the left 

and right lower surface panels of the 

wings, which could result in reduced 

structural integrity of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 32069, June 5, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

32069, June 5, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM 80 FR 32069, 

June 5, 2015). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Lockheed Martin Electra 

Service Bulletin 88/SB–707C, Revision 

C, dated April 30, 2014. The service 

information describes procedures for 

repetitive inspections for cracking of the 

left and right lower surface panels of the 

wings on the inboard and outboard 

sides of the buttock line (BL) 65 splice 

joint, and repair. This service 

information also describes procedures 

for a one-time bolt-hole eddy current 

inspection of all open holes for 

cracking, repair, and modification of the 

BL 65 wing root joint. 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 AD. 

Costs of Compliance 

We estimate that this AD affects 4 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


rmajette on DSK7SPTVN1PROD with RULES