8140 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 

manner by the inspection or maintenance 

program. We are issuing this AD to detect 

and correct such cracking, which could result 

in sudden decompression and loss of the 

airplane’s structural integrity. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

Except as required by paragraph (h) of this 

AD: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2880, dated 

December 3, 2014, do a detailed inspection 

of the upper closure fitting, strap, and 

doubler and a surface high frequency eddy 

current (HFEC) inspection of the upper 

closure fitting at the nose cargo door portal 

for cracking, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2880, dated December 3, 2014. 

Repeat the inspections at the time specified 

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

Alert Service Bulletin 747–53A2880, dated 

December 3, 2014. Do the applicable related 

investigative and corrective actions at the 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2880, dated December 3, 

2014. 

(h) Exceptions to the Service Information 

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

Boeing Alert Service Bulletin 747–53A2880, 

dated December 3, 2014, refers to a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 

compliance within the specific compliance 

time after the effective date of this AD. 

(2) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2880, dated 

December 3, 2014, specifies to contact Boeing 

for appropriate action: Before further flight, 

repair the cracking using a method approved 

in accordance with the procedures specified 

in paragraph (i) 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)(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, 

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. For a repair 

method 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)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

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. 

(j) Related Information 

For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@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 747– 

53A2880, dated December 3, 2014. 

(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 

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 February 

8, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03217 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2460; Directorate 

Identifier 2014–NM–163–AD; Amendment 

39–18396; AD 2016–04–02] 

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) 2010–26– 

10, which applied to certain The Boeing 

Company Model 747–200C, –200F, 

–400, –400D, and –400F series 

airplanes. AD 2010–26–10 required 

repetitive inspections for cracking of the 

lap joints, modification of certain lap 

joints, and certain post-repair 

inspections of the lap joints. This new 

AD adds new repetitive postmodification inspections for cracking in 

the lap joints, and repair if necessary. 

This AD was prompted by an evaluation 

by the design approval holder (DAH) 

which indicated that certain lap joints 

are subject to widespread fatigue 

damage (WFD). We are issuing this AD 

to detect and correct fatigue cracking in 

certain lap joints, which could result in 

rapid depressurization and consequent 

reduced structural integrity of the 

airplane. 

DATES: This AD is effective March 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 24, 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 


wgreen on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 8141 

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– 

2460. 

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– 

2460; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

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

425–917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–26–10, 

Amendment 39–16549 (75 FR 81427, 

December 28, 2010). AD 2010–26–10 

applied to certain The Boeing Company 

Model 747–200C, –200F, –400, –400D, 

and –400F series airplanes. The NPRM 

published in the Federal Register on 

July 9, 2015 (80 FR 39394). The NPRM 

was prompted by an evaluation by the 

DAH that indicated that certain lap 

joints are subject to WFD. The NPRM 

proposed to continue to require 

repetitive inspections for cracking of the 

lap joints, modification of certain lap 

joints, and certain post-repair 

inspections of the lap joints. The NPRM 

also proposed to require new repetitive 

post-modification inspections for 

cracking in the lap joints, and repair if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking in 

certain lap joints, which could result in 

rapid depressurization and consequent 

reduced 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 (80 FR 39394, 

July 9, 2015) and the FAA’s response to 

each comment. United Airlines 

concurred with the NPRM. 

Request To Correct Typographical 

Error 

Boeing asked that we correct the 

reference in the ‘‘Related Service 

Information under 1 CFR part 51’’ from 

‘‘. . . sections 41, 42, and 43’’ to ‘‘. . . 

sections 41, 42, and 46.’’ Boeing stated 

that section 43 should be section 46, 

and noted that this is a typographical 

error. 

We agree with the commenter’s 

request for the reason provided. We 

have corrected this typographical error 

in ‘‘Related Service Information under 1 

CFR part 51’’ accordingly. 

Request To Clarify Certain 

Requirements 

Boeing asked that we clarify 

paragraph (i)(1) of the proposed AD (80 

FR 39394, July 9, 2015) by including 

‘‘per Table 7’’ in that paragraph. Boeing 

also asked that we clarify paragraph 

(i)(3) of the proposed AD by including 

‘‘per Table 10’’ in that paragraph. 

We agree that clarification is 

necessary but we do not agree to change 

paragraphs (i)(1) and (i)(3) of this AD. 

Paragraph (i) of this AD specifies doing 

the applicable inspections in paragraphs 

(i)(1), (i)(2), or (i)(3) of this AD, in 

accordance with the Accomplishment 

Instructions of the referenced service 

information; and repeating the 

applicable inspections at the applicable 

times specified in Tables 7, 8, 9, and 10 

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

Boeing Alert Service Bulletin 747– 

53A2499, Revision 3, dated July 15, 

2014. In each of these tables the 

applicable groups are identified and 

match the groups identified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this 

AD. We refer to the tables in paragraph 

1.E., ‘‘Compliance,’’ of service 

information for the applicable 

compliance times and not for how to 

accomplish the required actions. 

Therefore, we have not changed this AD 

in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, with minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

39394, July 9, 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 39394, 

July 9, 2015). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014. The service 

information describes procedures for 

body skin lap joint inspections and 

modifications in sections 41, 42, and 46. 

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 120 

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 

Pre-modification inspections [retained 

action from AD 2010–26–10, Amendment 39–16549 (75 FR 81427, December 28, 2010)].

Up to 675 work-hours × $85 per hour = 

up to $57,375.

$0 Up to $57,375 per 

inspection cycle.

Up to $6,885,000 

per inspection 

cycle. 

Modification [retained action from AD 

2010–26–10, Amendment 39–16549 

(75 FR 81427, December 28, 2010)].

Up to 5,819 work-hours × $85 per hour 

= up to $494,615.

0 Up to $494,615 ...... Up to $59,353,800. 

New proposed post-modification inspections.Up to 105 work-hours × $85 per hour = 

up to $8,925.

0 Up to $8,925 per inspection cycle.Up to $1,071,000 

per inspection 

cycle. 


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8142 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 

We have received no definitive data 

that would enable us to provide a cost 

estimate 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 

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) 

2010–26–10, Amendment 39–16549 (75 

FR 81427, December 28, 2010), and 

adding the following new AD: 

2016–04–02 The Boeing Company: 

Amendment 39–18396; Docket No. 

FAA–2015–2460; Directorate Identifier 

2014–NM–163–AD. 

(a) Effective Date 

This AD is effective March 24, 2016. 

(b) Affected ADs 

This AD replaces AD 2010–26–10, 

Amendment 39–16549 (75 FR 81427, 

December 28, 2010). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–200C, –200F, –400, –400D, and 

–400F series airplanes; certificated in any 

category; as identified in Boeing Alert 

Service Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014. 

(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 

certain lap joints are subject to widespread 

fatigue damage. We are issuing this AD to 

detect and correct fatigue cracking in certain 

lap joints, which could result in rapid 

depressurization and consequent reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Lap Joint Inspections 

At the applicable time specified in Table 

1 and Table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014, except as required by paragraph 

(j)(1) of this AD: Do eddy current inspections 

for cracks in the skin of the lap joints, and 

do all applicable repairs, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2499, 

Revision 3, dated July 15, 2014, except as 

required by paragraph (j)(2) of this AD. Do all 

applicable repairs before further flight. 

Repeat the applicable inspections thereafter 

at intervals not to exceed those specified in 

Table 1 and Table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014. 

(h) Lap Joint Modification 

At the applicable time specified in Tables 

2, 4, 5, and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014, except as required by paragraph 

(j)(1) of this AD: Modify the applicable lap 

joints, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014, except as required by 

paragraph (j)(2) of this AD. Accomplishment 

of the modification required by this 

paragraph terminates the repetitive 

inspections required by paragraph (g) of this 

AD for the length of the modified lap joint. 

(i) Lap Joint Post-Modification Inspections 

At the applicable time specified in Tables 

7, 8, 9, and 10 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014, except as required by paragraph 

(j)(1) of this AD: Do the applicable 

inspections specified in paragraph (i)(1), 

(i)(2), or (i)(3) of this AD, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2499, 

Revision 3, dated July 15, 2014. Repeat the 

applicable inspections thereafter at the 

applicable times specified in Tables 7, 8, 9, 

and 10 of paragraph 1.E, ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2499, 

Revision 3, dated July 15, 2014. If any crack 

is found during any inspection, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(1) For airplanes identified as Groups 2 

through 5 and 8 through 10 in Boeing Alert 

Service Bulletin 747–53A2499, Revision 3, 

dated July 15, 2014: Internal detailed and 

surface high frequency eddy current (HFEC) 

inspections for any crack in the skin or 

internal doubler. 

(2) For airplanes identified as Groups 6, 11, 

and 19 in Boeing Alert Service Bulletin 747– 

53A2499, Revision 3, dated July 15, 2014: 

External detailed and low frequency eddy 

current inspections of the upper and lower 

skin panels for cracking, external detailed 

and HFEC inspections of the doubler for 

cracking, and internal detailed and HFEC 

inspections of the upper and lower skin 

panels for cracking (for airplanes with a 

stringer 6 lap joint modification installed 

between STA 340 and STA 400 as specified 

in Boeing Service Bulletin 747–53–2272); or 

internal detailed and surface HFEC 

inspections for any crack in the skin or 

internal doubler (for airplanes with lap joints 

modified as specified in Boeing Alert Service 

Bulletin 747–53A2499.) 

(3) For airplanes identified as Groups 1, 7, 

and 12 through 18 in Boeing Alert Service 

Bulletin 747–53A2499, Revision 3, dated July 

15, 2014: Internal detailed and surface HFEC 

inspections for any crack in the skin or 

internal doubler. 

(j) Exceptions to Service Bulletin Procedures 

(1) Where Boeing Alert Service Bulletin 

747–53A2499, Revision 3, dated July 15, 

2014, specifies a compliance time ‘‘after the 

Revision 3 date of this service bulletin,’’ this 

AD requires compliance within the specified 


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Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 8143 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2499, Revision 3, dated July 15, 

2014, specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(k) Credit for Previous Actions 

Actions done before the effective date of 

this AD using the service information 

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

AD are acceptable for compliance with the 

corresponding requirements of paragraphs (g) 

and (h) of this AD. 

(1) Boeing Alert Service Bulletin 747– 

53A2499, Revision 1, dated October 30, 2008, 

which is not incorporated by reference in this 

AD. 

(2) Boeing Alert Service Bulletin 747– 

53A2499, Revision 2, dated August 12, 2010, 

which was incorporated by reference in AD 

2010–26–10, Amendment 39–16549 (75 FR 

81427, December 28, 2010). 

(l) 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 (m)(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, 

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) AMOCs approved for AD 2010–26–10, 

Amendment 39–16549 (75 FR 81427, 

December 28, 2010), are approved as AMOCs 

for the corresponding provisions of 

paragraphs (g) and (h) this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

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 (n)(3) and (n)(4) of this AD. 

(n) 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 747– 

53A2499, Revision 3, dated July 15, 2014. 

(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 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 February 

7, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03219 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4803; Directorate 

Identifier 2015–CE–034–AD; Amendment 

39–18399; AD 2016–04–05] 

RIN 2120–AA64 

Airworthiness Directives; B–N Group 

Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

airworthiness directive (AD) 2014–03– 

18 for B–N Group Ltd. Models BN–2, 

BN–2A, BN–2A–2, BN–2A–3, BN–2A–6, 

BN–2A–8, BN–2A–9, BN–2A–20, BN– 

2A–21, BN–2A–26, BN–2A–27, BN–2B– 

20, BN–2B–21, BN–2B–26, BN–2B–27, 

BN2A MK. III, BN2A MK. III–2, and 

BN2A MK. III–3 airplanes. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as damage of the cable sliding 

end assembly and installation of the 

incorrect end fitting on engine control 

cable assemblies. We are issuing this AD 

to require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective March 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 24, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of April 1, 2014 (79 FR 

10340, February 25, 2014). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4803; or in person at the 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 service information identified in 

this final rule, contact Britten-Norman 

Aircraft Limited, Commodore House, 

Mountbatten Business Centre, Millbrook 

Road East, Southampton SO15 1HY, 

United Kingdom; telephone: +44 20 

3371 4000; fax: +44 20 3371 4001; 

email: info@bnaircraft.com; Internet: 

http://www.britten-norman.com/ 

customer-support/. You may view this 

referenced 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 Docket No. FAA–2015– 

4803. 

FOR FURTHER INFORMATION CONTACT: 

Raymond Johnston, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4159; fax: (816) 329–3047; email: 

raymond.johnston@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 B–N Group Ltd. Models BN–2, 

BN–2A, BN–2A–2, BN–2A–3, BN–2A–6, 

BN–2A–8, BN–2A–9, BN–2A–20, BN– 

2A–21, BN–2A–26, BN–2A–27, BN–2B– 

20, BN–2B–21, BN–2B–26, BN–2B–27, 

BN2A MK. III, BN2A MK. III–2, and 


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