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contains regulatory documents having general

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are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

5 

Vol. 82, No. 1 

Tuesday, January 3, 2017 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3698; Directorate 

Identifier 2015–NM–138–AD; Amendment 

39–18733; AD 2016–25–07] 

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 certain 

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 

is subject to widespread fatigue damage 

(WFD). This AD requires replacing the 

aft pressure bulkhead with a new, 

improved aft pressure bulkhead, and 

doing related investigative and 

corrective actions if necessary. We are 

issuing this AD to prevent the unsafe 

condition on these products. 

DATES: This AD is effective February 7, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 7, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; 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– 

3698. 

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– 

3698; 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 certain The Boeing Company 

Model 767–200 and –300 series 

airplanes. The NPRM published in the 

Federal Register on February 22, 2016 

(81 FR 8668) (‘‘the NPRM’’). The NPRM 

was prompted by an evaluation by the 

DAH indicating that the aft pressure 

bulkhead at Station 1582 is subject to 

WFD. The NPRM proposed to require 

replacing the aft pressure bulkhead with 

a new, improved aft pressure bulkhead, 

and doing related investigative and 

corrective actions if necessary. We are 

issuing this AD to prevent fatigue 

cracking in the radial web lap splices of 

the aft pressure bulkhead. Such cracking 

could result in rapid decompression and 

consequent reduced structural integrity 

of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Boeing and United Airlines supported 

the NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST01920SE does not 

affect compliance with the actions 

specified in the NPRM. 

We agree with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as (c)(1) and added 

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 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. 

Changes To This AD 

We have reviewed Boeing Alert 

Service Bulletin 767–53A0267, Revision 

1, dated August 4, 2016, and there are 

no substantial changes. Therefore, we 

have included Boeing Alert Service 

Bulletin 767–53A0267, Revision 1, 

dated August 4, 2016, in paragraphs (c), 

(g), (h), and (i) of this AD. We have also 

provided credit in paragraph (j) of this 

AD for actions done prior to the 

effective date of this AD using Boeing 

Alert Service Bulletin 767–53A0267, 

dated August 13, 2015. 

We have also revised paragraph (g) of 

this AD to clarify certain terminating 

actions. 

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 


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6 Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Rules and Regulations 

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 767–53A0267, Revision 1, 

dated August 4, 2016. The service 

information describes procedures for 

replacing the aft pressure bulkhead at 

Station 1582 of Section 48 with a new, 

improved aft pressure bulkhead, 

including all applicable related 

investigative and corrective actions. 

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 86 

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 

Replacement ........................... 1,541 work-hours × $85 per hour = $130,985 ....................... $646,889 $777,874 $66,897,164 

We have received no definitive data 

that enables us to provide cost estimates 

for the on-condition investigative and 

corrective 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): 

2016–25–07 The Boeing Company: 

Amendment 39–18733; Docket No. 

FAA–2016–3698; Directorate Identifier 

2015–NM–138–AD. 

(a) Effective Date 

This AD is effective February 7, 2017. 

(b) Affected ADs 

This AD affects the ADs specified in 

paragraphs (b)(1), (b)(2), and (b)(3) of this AD. 

(1) AD 2004–05–16, Amendment 39–13511 

(69 FR 10917, March 9, 2004). 

(2) AD 2004–14–19, Amendment 39–13728 

(69 FR 42549, July 16, 2004). 

(3) AD 2009–06–19, Amendment 39–15856 

(74 FR 12243, March 24, 2009). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 767–200 and –300 series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

767–53A0267, Revision 1, dated August 4, 

2016. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01920SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgSTC.nsf/0/

38B606833BBD98B386257FAA00602538

?OpenDocument&Highlight=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. 

(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 (DAH) indicating 

that the aft pressure bulkhead at Station 1582 

is subject to widespread fatigue damage 

(WFD). We are issuing this AD to prevent 

fatigue cracking in the radial web lap splices 

of the aft pressure bulkhead. Such cracking 

could result in rapid decompression and 

consequent reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement, Related Investigative and 

Corrective Actions, and Terminating Actions 

Before the accumulation of 60,000 total 

flight cycles, or within 36 months after the 

effective date of this AD, whichever occurs 

later, but not earlier than 37,500 total 

accumulated flight cycles: Replace the aft 

pressure bulkhead at Station 1582 of Section 

48 with a new, improved aft pressure 

bulkhead, and perform all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0267, Revision 1, dated August 4, 

2016; except as required by paragraph (h) of 

this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Accomplishing the 

replacement in this paragraph terminates all 

requirements of the ADs identified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

(1) AD 2004–05–16, Amendment 39–13511 

(69 FR 10917, March 9, 2004). 

(2) AD 2004–14–19, Amendment 39–13728 

(69 FR 42549, July 16, 2004). 

(3) AD 2009–06–19, Amendment 39–15856 

(74 FR 12243, March 24, 2009). 


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Federal Register / Vol. 82, No. 1 / Tuesday, January 3, 2017 / Rules and Regulations 7 

(h) Corrective Actions 

If any defect (e.g., rifling, gouging, nicks, or 

burrs, or excessive surface roughness) is 

found in any fastener hole (other than 

normally produced during a typical reaming 

operation), during accomplishment of any 

inspection (related investigative actions) 

required by this AD, and Boeing Alert 

Service Bulletin 767–53A0267, Revision 1, 

dated August 4, 2016, specifies to contact 

Boeing for repair instructions: Before further 

flight, repair in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(i) Exception to the Service Information 

Where Boeing Alert Service Bulletin 767– 

53A0267, Revision 1, dated August 4, 2016, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified time after the effective date of this 

AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 767–53A0267, 

dated August 13, 2015; which is not 

incorporated by reference in this AD. 

(k) 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 (l) 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 (h) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(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. If a step or sub-step is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

sub-step. 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. 

(l) 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. 

(m) 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– 

53A0267, Revision 1, dated August 4, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; 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 

November 25, 2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–29678 Filed 12–30–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0457; Directorate 

Identifier 2015–NM–084–AD; Amendment 

39–18751; AD 2016–25–25] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–11– 

15 for all BAE Systems (Operations) 

Limited Model 4101 airplanes. AD 

2012–11–15 required a one-time 

detailed inspection for cracks, 

corrosion, and other defects of the rear 

face of the wing rear spar, and repair if 

necessary. This new AD requires 

repetitive detailed inspections, and 

repair if necessary. This AD was 

prompted by new reports of cracking 

found in the wing rear spar and 

technical analysis results, which 

confirmed that the crack initiation and 

propagation are due to fatigue, with no 

indication of any other crack initiation 

mechanism (e.g., stress corrosion). We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 7, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 7, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact BAE 

Systems (Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 

1292 675704; email RApublications@

baesystems.com; Internet http://

www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 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– 

0457. 


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