67052 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 

747–53A2605, Revision 3, dated July 10, 

2013: This paragraph provides credit for the 

actions required by paragraphs (j)(1) and 

(k)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 747– 

53A2605, Revision 2, dated December 9, 

2011, which is not incorporated by reference 

in this AD. 

(n) 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 (o)(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. 

(4) AMOCs approved for inspections 

required by AD 2012–13–08, Amendment 

39–17110 (77 FR 40481, July 10, 2012) are 

approved as AMOCs for the corresponding 

inspection provisions of paragraphs (g), (h), 

and (i) of this AD. 

(5) AMOCs approved for AD 2012–13–08, 

Amendment 39–17110 (77 FR 40481, July 10, 

2012) that granted modification deviations 

are approved as AMOCs for the 

corresponding modification required by 

paragraph (j)(1) of this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

Seattle Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, WA 

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

917–6590; email: Nathan.P.Weigand@

faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(6) and (p)(7) of this AD. 

(p) 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 December 17, 2014. 

(i) Boeing Alert Service Bulletin 747– 

53A2605, Revision 3, dated July 10, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 14, 2012 (77 FR 

40481, July 10, 2012). 

(i) Boeing Alert Service Bulletin 747– 

53A2502, Revision 1, dated June 17, 2010. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on February 16, 2006 (71 

FR 1947, January 12, 2006). 

(i) Boeing Special Attention Service 

Bulletin 747–53–2502, dated April 21, 2005. 

(ii) Reserved. 

(6) 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. 

(7) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(8) 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 October 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26536 Filed 11–10–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0430; Directorate 

Identifier 2014–NM–083–AD; Amendment 

39–18014; AD 2014–22–09] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all the 

Boeing Company Model 767 airplanes. 

This AD was prompted by a report of a 

rotary actuator for the trailing edge (TE) 

flap that had slipped relative to its 

mating reaction ring, which is attached 

to the flap support rib. This AD requires 

repetitive inspections for corrosion of 

the fixed ring gear and reaction ring 

splines of the rotary actuator assembly 

for each support position, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct flap rotary actuator 

gear disengagement from its mating 

reaction ring. This disengagement with 

flaps extended could cause an 

uncommanded roll due to flap 

blowback, overload, or flap departure 

from the airplane, which could 

compromise safe flight and landing of 

the airplane. 

DATES: This AD is effective December 

17, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 17, 2014. 

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. 

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–2014– 

0430; 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: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6487; 

fax: 425–917–6590; email: 

Allen.Rauschendorfer@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 The Boeing Company Model 

767 airplanes. The NPRM published in 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 67053 

the Federal Register on July 9, 2014 (79 

FR 38797). The NPRM was prompted by 

a report of a rotary actuator for the TE 

flap that had slipped relative to its 

mating reaction ring, which is attached 

to the flap support rib. The NPRM 

proposed to require repetitive 

inspections for corrosion of the fixed 

ring gear and reaction ring splines of the 

rotary actuator assembly for each 

support position, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct flap rotary actuator 

gear disengagement from its mating 

reaction ring. This disengagement with 

flaps extended could cause an 

uncommanded roll due to flap 

blowback, overload, or flap departure 

from the airplane, which could 

compromise safe flight and landing of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 38797, 

July 9, 2014) and the FAA’s response to 

the comment. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing 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 specified in the NPRM (79 

FR 38797, July 9, 2014). 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

NPRM (79 FR 38797, July 9, 2014) as 

paragraph (c)(1) and added a 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 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. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 NPRM (79 FR 

38797, July 9, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 38797, 

July 9, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 389 

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 

Inspection .......................... 60 work-hours × $85 per hour = $5,100 

per inspection cycle.

$0 $5,100 per inspection 

cycle.

$1,983,900 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Actuator repair .............................. 4 work-hours × $85 per hour = $340 per actuator ............................ $0 $340 per actuator. 

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 

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: 


wreier-aviles on DSK5TPTVN1PROD with RULES
67054 Federal Register / Vol. 79, No. 218 / Wednesday, November 12, 2014 / Rules and Regulations 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2014–22–09 The Boeing Company: 

Amendment 39–18014 ; Docket No. 

FAA–2014–0430; Directorate Identifier 

2014–NM–083–AD. 

(a) Effective Date 

This AD is effective December 17, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 767–200, –300, –300F, and 

–400ER series airplanes, certificated in any 

category. 

(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 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

trailing edge (TE) flap rotary actuator that 

had slipped relative to its mating reaction 

ring, which is attached to the flap support 

rib. We are issuing this AD to detect and 

correct flap rotary actuator gear 

disengagement from its mating reaction ring. 

This disengagement with flaps extended 

could cause an uncommanded roll due to 

flap blowback, overload, or flap departure 

from the airplane, which could compromise 

safe flight and landing of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections, Related 

Investigative Actions, and Corrective 

Actions 

Except as provided by paragraph (h) of this 

AD, at the applicable time specified in 

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

Alert Service Bulletin 767–27A0229, dated 

March 4, 2014: Do a detailed inspection for 

corrosion of the rotary actuator assembly 

fixed ring gear and reaction ring splines for 

each support position; and do all applicable 

related investigative and corrective actions if 

necessary; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–27A0229, dated March 

4, 2014. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection of the 

rotary actuator assembly fixed ring gear and 

reaction ring splines for each support 

position thereafter at the applicable intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 767–27A0229, 

dated March 4, 2014. 

(h) Exception to the Requirements of 

Paragraph (g) of this AD 

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

Boeing Alert Service Bulletin 767–27A0229, 

dated March 4, 2014, specifies a compliance 

time ‘‘after the original issue date of this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time ‘‘after the effective date of this AD.’’ 

(i) 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 (j) 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) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from, done as part of other actions, or done 

using accepted methods different from those 

identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(j) Related Information 

For more information about this AD, 

contact Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

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

6590; email: Allen.Rauschendorfer@faa.gov. 

(k) 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. 

(i) Boeing Alert Service Bulletin 767– 

27A0229, dated March 4, 2014. 

(ii) Reserved. 

(3) For Boeing 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. 

(4) 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. 

(5) 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 October 

28, 2014. 

Jeffrey E. Duven 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26440 Filed 11–10–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 43 

[Docket No. FAA–2000–8017, Amdt. No. 43– 

38A] 

RIN 2120–AH11 

Disposition of Life Limited Aircraft 

Parts; Technical Amendment 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: The FAA is correcting a final 

rule published in the Federal Register 

on January 15, 2002 (67 FR 2110). In 

that rule, the FAA amended its 

regulations to require that all persons 

who remove any life-limited aircraft 

part safely control that part, to deter the 

installation of that part after it has 

reached its life limit. The rule reduced 

the risk of life-limited parts being used 


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