Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Rules and Regulations 10465 

having P/N MA20A1001–1 (S343T003–39) 

for the fuel tanks is installed: Within 60 

months after the effective date of this AD, 

replace the affected MOV actuator with a 

serviceable, FAA-approved MOV actuator 

other than one having P/N MA20A1001–1 

(S343T003–39). 

Note 1 to paragraph (h) of this AD: 

Guidance on replacing the affected MOV 

actuator may be found in the Boeing 767 

Aircraft Maintenance Manual or the Boeing 

777 Aircraft Maintenance Manual, as 

applicable. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an MOV actuator having 

P/N MA20A1001–1 (S343T003–39) on any 

airplane. 

(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. 

(k) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6509; fax: 425– 

917–6590; email: rebel.nichols@faa.gov. 

(2) 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. 

(l) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on February 

16, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04033 Filed 2–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2455; Directorate 

Identifier 2014–NM–180–AD; Amendment 

39–18415; AD 2016–04–21] 

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) 2008–26– 

07 for all The Boeing Company Model 

DC–8–11, DC–8–12, DC–8–21, DC–8–31, 

DC–8–32, DC–8–33, DC–8–41, DC–8–42, 

and DC–8–43 airplanes; Model DC–8–50 

series airplanes; Model DC–8F–54 and 

DC–8F–55 airplanes; Model DC–8–60 

series airplanes; Model DC–8–60F series 

airplanes; Model DC–8–70 series 

airplanes; and Model DC–8–70F series 

airplanes. AD 2008–26–07 required 

repetitive inspections of the lower skin 

and stringers at certain stations, and 

corrective actions if necessary. This new 

AD continues to require the actions 

specified in AD 2008–26–07 and also 

requires an eddy current high frequency 

(ETHF) inspection for cracks of the 

fastener open holes common to the 

lower skins, stringers, and splice fittings 

at a certain station; installation of 

external doublers and fasteners and 

repetitive eddy current low frequency 

(ETLF) inspections around the fasteners 

for any crack; and corrective actions if 

necessary. This AD was prompted by 

certain mandated programs intended to 

support the airplane reaching its limit of 

validity of the engineering data that 

support the established structural 

maintenance program. We are issuing 

this AD to detect and correct cracks in 

the lower skins, stringers, and fastener 

holes of the splice fittings, which could 

result in the loss of structural integrity 

of the airplane. 

DATES: This AD is effective April 5, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 5, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 28, 2009 (73 FR 

78946, December 24, 2008). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; 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–2015– 

2455. 

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– 

2455; 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 

Document 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: 

Chandra Ramdoss, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; telephone: 

562–627–5239; fax: 562–627–5210; 

email: Chandraduth.Ramdoss@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–26–07, 

Amendment 39–15773 (73 FR 78946, 

December 24, 2008), (‘‘AD 2008–26– 

07’’). AD 2008–26–07 applied to all 

McDonnell Douglas Model DC–8–11, 

DC–8–12, DC–8–21, DC–8–31, DC–8–32, 

DC–8–33, DC–8–41, DC–8–42, and DC– 

8–43 airplanes; Model DC–8–50 series 

airplanes; Model DC–8F–54 and DC– 

8F–55 airplanes; Model DC–8–60 series 

airplanes; Model DC–8–60F series 

airplanes; Model DC–8–70 series 

airplanes; and Model DC–8–70F series 

airplanes. The NPRM published in the 

Federal Register on July 2, 2015 (80 FR 

38038) (‘‘the NPRM’’). The NPRM was 

prompted by certain mandated 

programs intended to support the 

airplane reaching its limit of validity of 


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10466 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Rules and Regulations 

the engineering data that support the 

established structural maintenance 

program. The NPRM proposed to 

continue to require the actions specified 

in AD 2008–26–07 and also to require 

an ETHF inspection for cracks of the 

fastener open holes common to the 

lower skins, stringers, and splice fittings 

at a certain station; installation of 

external doublers and fasteners and 

repetitive ETLF inspections around the 

fasteners for any crack; and corrective 

actions if necessary. We are issuing this 

AD to detect and correct cracks in the 

lower skins, stringers, and fastener holes 

of the splice fittings, which 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 comment 

received on the NPRM and the FAA’s 

response to the comment. 

Request To Clarify the Actions in 

Paragraph (j)(1) of the Proposed AD 

Boeing requested that we clarify 

paragraph (j)(1) of the proposed AD. 

Boeing stated that paragraph (j)(1) of the 

proposed AD does not specify what to 

inspect or how to inspect. Boeing 

recommended that a description similar 

to that of paragraph (j)(2) of the 

proposed AD be included in paragraph 

(j)(1) of the proposed AD. 

We agree with the request to clarify 

the inspection requirements. Paragraph 

(j)(l) of the AD is for airplanes that have 

previous structural repairs at the lower 

skins, stringers, and splice. For those 

airplanes, because the details of the 

configuration are not known, a specific 

description of the area to be inspected 

cannot be given. Paragraph (j)(2) of this 

AD provides specific inspections for 

certain airplanes because those 

inspections are described in Boeing 

Service Bulletin DC8–57–104, dated 

August 18, 2014. However, that service 

information does not provide specific 

inspection areas for airplanes identified 

in paragraph (j)(1) of this AD. Therefore, 

for the inspection and applicable 

corrective actions, paragraph (j)(1) of 

this AD requires that the operator use a 

method approved in the accordance 

with the procedures specified in 

paragraph (m) of this AD. We have 

revised paragraph (j)(1) of this AD to 

specify the general inspection area, 

which includes the lower skins, 

stringers, and splice fittings. 

Clarification of Actions Specified in 

Paragraph (k) of This AD. 

Paragraph (k) of the NPRM referred to 

Boeing Service Bulletin DC8–57–104, 

dated August 18, 2014, for the 

compliance times for the actions 

required by that paragraph but did not 

include a reference for the installation 

and inspections required by paragraph 

(k) of this AD. We have revised 

paragraph (k) of this AD to refer to 

Boeing Service Bulletin DC8–57–104, 

dated August 18, 2014, as the 

appropriate source of service 

information for accomplishing the 

installation and inspections. 

Conclusion 

We reviewed the relevant data 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 Service Bulletin 

DC8–57–104, dated August 18, 2014. 

The service information describes 

procedures for certain airplanes for an 

ETHF inspection for cracks of the 

fastener open holes common to the 

lower skins, stringers, and splice fittings 

at a certain station; installation of 

external doublers and fasteners and 

repetitive ETLF inspections around the 

fasteners for any crack; 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 12 

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 [retained actions from AD 2008-26-07, 

Amendment 39–15773 (73 FR 78946, December 

24, 2008)].

6 work-hours × $85 per 

hour = $510 per inspection cycle.

$0 $510 $6,120 per inspection 

cycle. 

ETHF Inspection [new action] .................................... 8 work-hours × $85 per 

hour = $680 per inspection cycle.

$0 $680 $8,160 per inspection 

cycle. 

We estimate the following costs to do 

any necessary certain follow-on actions 

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 actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Installation of External Doubler ................................................. 5 work-hour × $85 per hour = 

$425.

$20,000 $20,425. 

Repetitive ETLF inspection ....................................................... 8 work-hour × $85 per hour = 

$680 per inspection cycle.

$0 $680 per inspection cycle. 


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Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Rules and Regulations 10467 

For all actions and repairs on Groups 

1–3, Configuration 1 Airplanes, we have 

received no definitive data that would 

enable us to 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 

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) 

2008–26–07, Amendment 39–15773 (73 

FR 78946, December 24, 2008), and 

adding the following new AD: 

2016–04–21 The Boeing Company: 

Amendment 39–18415; Docket No. 

FAA–2015–2455; Directorate Identifier 

2014–NM–180–AD. 

(a) Effective Date 

This AD is effective April 5, 2016. 

(b) Affected ADs 

This AD replaces AD 2008–26–07, 

Amendment 39–15773 (73 FR 78946, 

December 24, 2008). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model DC–8–11, DC–8–12, DC–8– 

21, DC–8–31, DC–8–32, DC–8–33, DC–8–41, 

DC–8–42, DC–8–43, DC–8–51, DC–8–52, DC– 

8–53, DC–8–55, DC–8F–54, DC–8F–55, DC– 

8–61, DC–8–62, DC–8–63, DC–8–61F, DC–8– 

62F, DC–8–63F, DC–8–71, DC–8–72, DC–8– 

73, DC–8–71F, DC–8–72F, and DC–8–73F 

airplanes; certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by certain 

mandated programs intended to support the 

airplane reaching its limit of validity of the 

engineering data that support the established 

structural maintenance program. We are 

issuing this AD to detect and correct cracks 

in the lower skins, stringers, and fastener 

holes of the splice fittings, which 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) Retained Repetitive Inspections With No 

Changes 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–26–07, Amendment 

39–15773 (73 FR 78946, December 24, 2008), 

with no changes. At the times specified in 

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

Alert Service Bulletin DC8–57A102, dated 

February 12, 2008, except as provided by 

paragraph (h) of this AD, do the applicable 

inspections for fatigue cracking of the lower 

skin and stringers at stations Xw = 408 and 

Xw = ¥408, and do all applicable corrective 

actions, by accomplishing all applicable 

actions specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC8–57A102, dated February 12, 2008. Do all 

corrective actions before further flight. 

Thereafter, repeat the inspections at the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin DC8–57A102, dated February 12, 

2008, until paragraph (j) of this AD is done. 

(h) Retained Exception for Compliance Time 

With No Changes 

This paragraph restates the exception 

specified in paragraph (g) of AD 2008–26–07, 

Amendment 39–15773 (73 FR 78946, 

December 24, 2008), with no changes. Where 

Boeing Alert Service Bulletin DC8–57A102, 

dated February 12, 2008, specifies a 

compliance time ‘‘after the date on this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after January 28, 2009 (the effective date 

of AD 2008–26–07). 

(i) Retained Exception for Corrective Action 

With No Changes 

This paragraph restates the exception 

specified in paragraph (h) of AD 2008–26–07, 

Amendment 39–15773 (73 FR 78946, 

December 24, 2008), with no changes. If any 

cracking is found during any inspection 

required by paragraph (g) of this AD, and 

Boeing Alert Service Bulletin DC8–57A102, 

dated February 12, 2008, 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 (m) of this AD. 

(j) New Inspections and Corrective Action 

(1) For Groups 1–3, Configuration 1 

airplanes identified in Boeing Service 

Bulletin DC8–57–104, dated August 18, 2014: 

At the applicable time specified in paragraph 

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

Bulletin DC8–57–104, dated August 18, 2014, 

except as required in paragraph (l) of this AD, 

do an inspection for any cracking of the 

lower skins, stringers, and splice fittings, and 

do all applicable corrective actions, using a 

method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

(2) For Groups 1–3, Configuration 2 

airplanes identified in Boeing Service 

Bulletin DC8–57–104, dated August 18, 2014: 

At the applicable time specified in paragraph 

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

Bulletin DC8–57–104, dated August 18, 2014, 

except as required in paragraph (l) of this AD, 

do an eddy current high frequency (ETHF) 

inspection for any cracking of the fastener 

open holes common to the lower skins, 

stringers, and splice fittings at station Xw = 

408 and Xw = ¥408 from stringer 51 to 

stringer 65, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC8–57–104, dated August 

18, 2014. If any cracking is found, before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (m) of this AD. 

(k) New Doubler and Fastener Installation 

and Eddy Current Low Frequency (ETLF) 

Inspection of the External Doubler and 

Corrective Action 

If no crack is found during the inspection 

required by paragraph (j)(2) of this AD: At the 

applicable times specified in paragraph 1.E., 


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10468 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Rules and Regulations 

‘‘Compliance,’’ of Boeing Service Bulletin 

DC8–57–104, dated August 18, 2014, install 

external doublers and fasteners, and do an 

external doubler ETLF inspection around the 

fasteners for any cracking, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin DC8–57–104, dated 

August 18, 2014. Repeat the external ETLF 

inspection at the applicable intervals 

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

Service Bulletin DC8–57–104, dated August 

18, 2014. If any cracking is found during any 

ETLF inspection required by this paragraph, 

before further flight, repair the crack using a 

method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

(l) Exception to the Compliance Time 

Where Boeing Service Bulletin DC8–57– 

104, dated August 18, 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. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (n) of this AD. Information may be 

emailed to 9-ANM-LAACO-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, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2008–26–07, 

Amendment 39–15773 (73 FR 78946, 

December 24, 2008), are approved as AMOCs 

for the corresponding provisions of this AD. 

(5) Except as required by paragraphs (j) and 

(k) of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (m)(5)(i) and (m)(5)(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. 

(n) Related Information 

For more information about this AD, 

contact Chandra Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles ACO, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

telephone: 562–627–5239; fax: 562–627– 

5210; email: Chandraduth.Ramdos@faa.gov. 

(o) 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 April 5, 2016. 

(i) Boeing Service Bulletin DC8–57–104, 

dated August 18, 2014. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on January 28, 2009 (73 FR 

78946, December 24, 2008). 

(i) Boeing Alert Service Bulletin DC8– 

57A102, dated February 12, 2008. 

(ii) Reserved. 

(5) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, 3855 Lakewood 

Boulevard, MC D800–0019, Long Beach, CA 

90846–0001; telephone 206–544–5000, 

extension 2; fax 206–766–5683; Internet 

https://www.myboeingfleet.com. 

(6) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on February 

15, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04035 Filed 2–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1270; Directorate 

Identifier 2014–NM–222–AD; Amendment 

39–18412; AD 2016–04–18] 

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 747–100, 

–200B, –200C, –200F, –300, –400, 

–400D, and –400F series airplanes. This 

AD was prompted by reports of 

significant fuselage skin damage at 

certain parts of the dorsal fairing, due to 

wear from the dorsal fairing. This AD 

requires repetitive detailed inspections 

for wear and cracks of the fuselage skin 

under the dorsal fairing, and related 

investigative and corrective actions if 

necessary. This AD also requires 

repetitive post-repair external surface 

high frequency eddy current inspections 

of the blended areas of the skin and 

detailed inspections of the unrepaired 

areas, and related investigative and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

fuselage skin damage of the dorsal 

fairing area, which could result in skin 

cracking and consequent 

depressurization of the airplane. 

DATES: This AD is effective April 5, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 5, 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–2015– 

1270. 


asabaliauskas on DSK5VPTVN1PROD with RULES