58816 Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations 

(i). Textron Aviation, Inc. (Cessna) Multiengine Service Bulletin (SB) No. MEB–27–02, 

Revision 1, dated June 15, 2016. 

(ii) Reserved. 

(4) For Textron Aviation, Inc. (Cessna) 

service information identified in this AD, 

contact Textron Aviation Customer Service, 

P.O. Box 7706, Wichita, Kansas 67277; 

telephone: (316) 517–5800; fax: (316) 517– 

7271; email: customercare@

cessna.textron.com; Internet: https://

support.cessna.com/custsupt/csupport/ 

newlogin.jsp. 

(5) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. It 

is also available on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2016–8992. 

(6) 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 Kansas City, Missouri, on August 

17, 2016. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–20073 Filed 8–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4221; Directorate 

Identifier 2015–NM–167–AD; Amendment 

39–18619; AD 2016–17–06] 

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 767–200 and 

–300 series airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the aft pressure bulkhead 

web to pressure chord joint is subject to 

widespread fatigue damage (WFD). This 

AD requires repetitive high frequency 

eddy current (HFEC) inspections of the 

aft pressure bulkhead web at fasteners 

common to the bulkhead web and 

pressure chord, around the entire 

circumference of the pressure chord, for 

any crack, and repair of cracks. We are 

issuing this AD to detect and correct 

cracks in the aft pressure bulkhead web. 

Such cracking could result in the loss of 

structural integrity of the airplane. 

DATES: This AD is effective September 

30, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 30, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

4221. 

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–2016– 

4221; 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: 

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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

767–200 and –300 series airplanes. The 

NPRM published in the Federal 

Register on March 8, 2016 (81 FR 

12047) (‘‘the NPRM’’). The NPRM was 

prompted by an evaluation by the DAH 

indicating that the aft pressure bulkhead 

web to pressure chord joint is subject to 

WFD. The NPRM proposed to require 

repetitive HFEC inspections of the aft 

pressure bulkhead web at fasteners 

common to the bulkhead web and 

pressure chord, around the entire 

circumference of the pressure chord, for 

any crack, and repair of cracks. We are 

issuing this AD to detect and correct 

cracks in the aft pressure bulkhead web. 

Such cracking could result in the loss of 

structural integrity of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response. Boeing and United Airlines 

supported the NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing supplemental type 

certificate (STC) ST01920SE does not 

affect the actions specified in the 

proposed AD. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1), and 

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

to state that installation of STC 

ST01920SE 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 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 NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

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 767–53A0268, dated April 1, 

2015. The service information describes 

procedures for HFEC inspections of the 

aft pressure bulkhead web at fasteners 


ehiers on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations 58817 

common to the bulkhead web and 

pressure chord, around the entire 

circumference of the pressure chord, for 

any crack, and repair of cracks. 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. 

Costs of Compliance 

We estimate that this AD affects 296 

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 ................................................................................ 57 work-hours × $85 per hour 

= $4,845.

$0 $4,845 $1,434,120 

The size of any repair area needs to 

be determined before material and 

work-hour costs can be calculated, so 

we cannot provide cost estimates for the 

on-condition actions specified in this 

AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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 adding 

the following new airworthiness 

directive (AD): 

2016–17–06 The Boeing Company: 

Amendment 39–18619; Docket No. 

FAA–2016–4221; Directorate Identifier 

2015–NM–167–AD. 

(a) Effective Date 

This AD is effective September 30, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 767–200 and –300 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_AML.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 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the aft pressure bulkhead web to pressure 

chord joint is subject to widespread fatigue 

damage. We are issuing this AD to detect and 

correct cracks in the aft pressure bulkhead 

web. Such cracking could result in the loss 

of structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Except as required by paragraph (h) of this 

AD, at the applicable time specified in 

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

Alert Service Bulletin 767–53A0268, dated 

April 1, 2015, perform a surface high 

frequency eddy current (HFEC) inspection for 

cracking of the aft pressure bulkhead web at 

fasteners common to the bulkhead web and 

pressure chord, around the entire 

circumference of the pressure chord, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0268, dated April 1, 2015. For this 

AD, Group 2, Configuration 2, as specified in 

Boeing Alert Service Bulletin 767–53A0268, 

dated April 1, 2015, includes airplanes with 

the aft pressure bulkhead replaced as 

specified in Boeing Alert Service Bulletin 

767–53A0267. Repeat the inspection 

thereafter at the applicable time specified in 

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

Alert Service Bulletin 767–53A0268, dated 

April 1, 2015. 

(h) Service Information Exception 

Where Boeing Alert Service Bulletin 767– 

53A0268, dated April 1, 2015, 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) Crack Repair 

If any crack is found during any inspection 

required by paragraph (g) of this AD, before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

Although Boeing Alert Service Bulletin 767– 

53A0268, dated April 1, 2015, specifies to 

contact Boeing for repair instructions, and 

specifies that action as ‘‘RC’’ (Required for 

Compliance), this AD requires repair as 

specified in this paragraph. Installation of a 


ehiers on DSK5VPTVN1PROD with RULES
58818 Federal Register / Vol. 81, No. 166 / Friday, August 26, 2016 / Rules and Regulations 

repair terminates the inspections required by 

paragraph (g) of this AD in the area covered 

by the repair only. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

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

this AD: For service information that 

contains steps that are labeled as RC, the 

provisions of paragraphs (j)(4)(i) and (j)(4)(ii) 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

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

917–6590; email: wayne.lockett@faa.gov. 

(l) 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– 

53A0268, dated April 1, 2015. 

(ii) Reserved. 

(3) 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. 

(4) 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. 

(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 August 

16, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate Aircraft Certification Service. 

[FR Doc. 2016–20075 Filed 8–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0463; Directorate 

Identifier 2015–NM–155–AD;Amendment 

39–18623; AD 2016–17–10] 

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 777 airplanes. 

This AD was prompted by a report of an 

incident involving a landing in which 

the pilots needed to input corrections 

due to airplane yaw and roll to the right; 

the main landing gear (MLG) aft 

trunnion pin was later found to be 

fractured. This AD requires 

identification and replacement of 

certain MLG aft trunnion pins. We are 

issuing this AD to prevent a fractured 

MLG aft trunnion pin, which could 

result in collapse of the MLG and 

consequent loss of control of the 

airplane during landing. 

DATES: This AD is effective September 

30, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 30, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone: 206–544–5000, 

extension 1; fax: 206–766–5680; 

Internet: https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0463. 

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–2016– 

0463; 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: Eric 

Lin, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6412; fax: 415– 

917–6590; email: eric.lin@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 

777 airplanes. The NPRM published in 

the Federal Register on February 18, 

2016 (81 FR 8164) (‘‘the NPRM’’). The 

NPRM was prompted by a report of an 

incident involving a landing in which 

the pilots needed to input corrections 

due to airplane yaw and roll to the right; 

the MLG aft trunnion pin was later 

found to be fractured. The NPRM 

proposed to require identification and 

replacement of certain MLG aft trunnion 

pins. We are issuing this AD to prevent 

a fractured MLG aft trunnion pin, which 

could result in collapse of the MLG and 

consequent loss of control of the 

airplane during landing. 


ehiers on DSK5VPTVN1PROD with RULES