Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72573 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A330–53–3206, 

Revision 03, dated February 28, 2014. 

(ii) Airbus Service Bulletin A340–53–4208, 

Revision 03, dated February 28, 2014. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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 October 

30, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28895 Filed 11–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1266; Directorate 

Identifier 2014–NM–151–AD; Amendment 

39–18327; AD 2015–23–11] 

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, 

747–100B, 747–100B SUD, 747–200B, 

747–300, 747SR, and 747SP series 

airplanes. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that certain 

fuselage skin lap joints are subject to 

widespread fatigue damage (WFD). This 

AD requires repetitive post-modification 

inspections for cracking of the skin or 

internal doubler along the edge fastener 

rows of the modification, and repair if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking in 

certain fuselage skin lap joints, which 

could result in rapid depressurization of 

the airplane. 

DATES: This AD is effective December 

28, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 28, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1266. 

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– 

1266; 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 by adding an AD that would 

apply to certain The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–300, 747SR, and 

747SP series airplanes. The NPRM 

published in the Federal Register on 

May 5, 2015 (80 FR 25630). The NPRM 

was prompted by an evaluation by the 

DAH indicating that certain fuselage 

skin lap joints are subject to WFD. The 

NPRM proposed to require repetitive 

post-modification inspections for 

cracking of the skin or internal doubler 

along the edge fastener rows of the 

modification, and repair if necessary. 

We are issuing this AD to detect and 

correct fatigue cracking in certain 

fuselage skin lap joints, which could 

result in rapid depressurization 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 25630, 

May 5, 2015) and the FAA’s response to 

each comment. 

Request To Remove Warranty 

Statement 

Boeing requested that we remove the 

statement that ‘‘some of the costs of this 

proposed AD may be covered under 

warranty’’ in the Costs of Compliance 

section of the NPRM (80 FR 25630, May 

5, 2015). Boeing stated that the actions 

in the NPRM are not covered by 

warranty. 

We agree with the commenter’s 

request. We have revised the Costs of 

Compliance section of this final rule 

accordingly. 

Request To Revise Paragraph Headings 

Boeing requested that we revise the 

headings of paragraphs (g), (h), (j), and 

(k) of the proposed AD (80 FR 25630, 

May 5, 2015) by removing reference to 

the inspections as ‘‘repetitive’’ or 

‘‘initial.’’ Boeing stated that these 

revisions will provide consistency 

among paragraph headings because 

paragraphs (g), (j), and (k) of the 

proposed AD do not have an initial 

inspection program, yet paragraph (h) of 

the proposed AD has only an initial 

inspection. 

We acknowledge the commenter’s 

concern and agree to clarify the 

headings. We do not presume that the 

term ‘‘repetitive’’ necessarily excludes 

the initial action. An action cannot be 

repeated without accomplishment of the 

initial action. In addition, in many ADs 

we use the term ‘‘repetitive’’ actions for 

paragraphs that include the initial 

action and repetitive actions. Paragraphs 

(g), (j), and (k) of this AD include both 

a sentence specifying the initial 

inspection and a sentence specifying the 

repetitive inspections. We have not 

changed this AD in this regard. 

Request To Clarify Compliance Time 

Boeing requested that we clarify the 

compliance time in paragraphs (g), (h), 

(j), and (k) of the proposed AD (80 FR 


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72574 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 

25630, May 5, 2015) by revising ‘‘at the 

applicable time’’ to ‘‘at the applicable 

time and repeat intervals.’’ Boeing 

stated that these revisions would clarify 

that the applicable time also includes 

the repeat intervals per Boeing Alert 

Service Bulletin 747–53A2367, Revision 

5, dated July 8, 2014. 

We do not agree to combine the initial 

inspection and the repetitive inspection 

times into one statement because ADs 

typically call out initial inspections and 

repetitive inspections in separate 

sentences. Paragraph (h) of this AD 

specifies only an initial inspection. 

Paragraphs (g), (j), and (k) of this AD 

specifies an initial inspection and states 

that the repetitive inspections are for the 

unrepaired areas, which are to be done 

at the applicable times specified in 

Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014. 

We have not changed this AD in this 

regard. 

Request To Delete the Unrepaired Area 

Statement From Paragraphs (g) (j) and 

(k) of the Proposed AD (80 FR 25630, 

May 5, 2015) 

Boeing requested that we delete the 

last sentence in paragraphs (g), (j), and 

(k) of the proposed AD (80 FR 25630, 

May 5, 2015), which states ‘‘In 

unrepaired areas, repeat the . . . 

inspections for cracks . . . .’’ Boeing 

stated that the sentence is confusing as 

the unrepaired area case is actually for 

no cracks found in the modification area 

after doing the inspection as specified in 

the applicable tables 3, 5, and 6 of 

Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014. 

Boeing explained that the proposed AD 

wording may cause confusion when 

information is provided in a different 

format than the service bulletin tables. 

We do not agree with the commenter’s 

request because the text ‘‘in unrepaired 

areas’’ matches the text in Boeing Alert 

Service Bulletin 747–53A2367, Revision 

5, dated July 8, 2014. Paragraphs (g), (j), 

and (k) of this AD specify doing actions 

at the applicable time specified in tables 

3, 5, and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, 

dated July 8, 2014. In these tables, the 

compliance time is specified for the 

actions required for the unrepaired area. 

We have not revised this AD in this 

regard. 

Request To Combine Paragraphs 

Boeing requested that we combine 

paragraphs (h) and (i) of the proposed 

AD (80 FR 25630, May 5, 2015) by 

deleting paragraph (i) of the proposed 

AD and revising paragraph (h) of the 

proposed AD from ‘‘at the applicable 

time’’ to ‘‘at the applicable time and 

repeat intervals.’’ Boeing explained that 

it is confusing to have separate 

paragraphs address initial and repetitive 

inspections for a particular aircraft as 

both initial and repetitive inspections 

are addressed within table 4 of Boeing 

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

We acknowledge that table 4 of 

Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014, 

contains compliance times for both 

initial and repetitive inspections. 

However, we do not agree with the 

commenter’s request because the AD 

includes separate paragraphs in order to 

clarify the repetitive inspection 

intervals. For the initial inspections, 

table 4 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014, 

specifies two crack conditions, which 

are based on the number of fight cycles 

on the airplane since stringer 6 external 

doublers were installed. To aid the 

operators in determining which 

repetitive inspection(s) they are 

required to do, this AD provides the 

repetitive inspections (as restated from 

the NPRM (80 FR 25630, May 5, 2015)), 

depending on the applicable condition, 

in separate repetitive inspection 

paragraphs (paragraphs (i)(1) and (i)(2) 

of this AD). We have not changed this 

AD in this regard. 

Request To Revise External Inspection 

Wording 

Boeing requested that we remove the 

word ‘‘external’’ from paragraph (h) of 

the proposed AD (80 FR 25630, May 5, 

2015), which specified ‘‘external 

detailed, low frequency eddy current, 

and high frequency eddy current 

inspections.’’ Boeing explained that if 

paragraphs (h) and (i) of the proposed 

AD are combined, both external and 

internal detailed inspections are 

required. Boeing stated that removing 

‘‘external’’ from the inspection direction 

would therefore cover all airplane 

conditions. 

As stated previously, we do not agree 

to combine paragraphs (h) and (i) of this 

AD into one paragraph. Therefore, the 

terminology in paragraph (h) of this AD 

matches Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 

2014, which specifies doing external 

detailed, low frequency eddy current 

(LFEC), and high frequency eddy 

current (HFEC) inspections for cracks. 

We have not changed this AD in this 

regard. 

Request To Revise Headings of 

Paragraphs (h), (i), and (j) of the 

Proposed AD (80 FR 25630, May 5, 

2015) 

Boeing requested that we revise the 

headings of paragraphs (h), (i), and (j) of 

the proposed AD (80 FR 25630, May 5, 

2015) by adding a reference to the 

applicable service information. Boeing 

stated that these changes will add 

consistency among paragraphs (h), (i), 

and (j) of the proposed AD in 

identifying an installed external doubler 

modification. 

We agree with the commenter’s 

request. We have revised the headings 

of paragraphs (h), (i), and (j) of this AD 

accordingly. 

Request To Correct Typographical 

Error 

Boeing noted that a phrase describing 

the major action in paragraph (j) of the 

proposed AD (80 FR 25630, May 5, 

2015) was duplicated and asked that we 

correct this. 

We agree with the commenter’s 

request. We have revised paragraph (j) 

of this AD accordingly. 

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 (80 FR 

25630, May 5, 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 25630, 

May 5, 2015). 

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 747–53A2367, Revision 5, 

dated July 8, 2014. This service 

information describes procedures for 

inspections and repair for cracks in the 

skin and doublers along the edge 

fastener rows of modifications in the 

fuselage. 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 of this AD. 


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Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72575 

Costs of Compliance 

We estimate that this AD affects 50 

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 

Post-modification inspection ........ 124 work-hours × $85 per hour = $10,540 

per inspection cycle.

$0 $10,540 per inspection cycle.$527,000 per inspection cycle. 

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 

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): 

2015–23–11 The Boeing Company: 

Amendment 39–18327; Docket No. 

FAA–2015–1266; Directorate Identifier 

2014–NM–151–AD. 

(a) Effective Date 

This AD is effective December 28, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–300, 747SR, and 747SP series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 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 fuselage skin lap joints are subject to 

widespread fatigue damage. We are issuing 

this AD to detect and correct fatigue cracking 

in certain fuselage skin lap joints, which 

could result in rapid depressurization of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Post-Modification Inspections 

for Airplane Groups 1 Through 3, 7, and 8 

For airplanes identified as Groups 1 

through 3, 7, and 8 in Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014: Except as provided by paragraph (m) 

of this AD, at the applicable time specified 

in table 3 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014, do 

internal detailed and surface high frequency 

eddy current (HFEC) inspections for cracks in 

the skin and internal doubler along the edge 

fastener rows of the modification, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 2014. 

In unrepaired areas, repeat the internal 

detailed and surface HFEC inspections for 

cracks in the skin or internal doubler along 

the edge fastener rows of the modification 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(h) Initial Post-Modification Inspections for 

Airplane Groups 4 Through 6, and 9 

Through 11, With External Doublers 

Installed as Specified in Boeing Service 

Bulletin 747–53–2272 

For airplanes identified as Groups 4 

through 6, and 9 through 11, in Boeing Alert 

Service Bulletin 747–53A2367, Revision 5, 

dated July 8, 2014, with external doublers 

installed as specified in Boeing Service 

Bulletin 747–53–2272: Except as provided by 

paragraph (m) of this AD, at the applicable 

time specified in table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014, do external detailed, low frequency 

eddy current (LFEC), and HFEC inspections 

for cracks in the skin and external doubler, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 2014. 

(i) Repetitive Post-Modification Inspections 

for Airplane Groups 4 Through 6, and 9 

Through 11 With External Doublers Installed 

as Specified in Boeing Service Bulletin 747– 

53–2272 

For airplanes with no crack findings during 

the inspections required by paragraph (h) of 

this AD: Do the applicable actions required 

by paragraphs (i)(1) and (i)(2) of this AD. 

(1) For airplanes with less than 15,000 

flight cycles since stringer 6 external 

doublers were installed, as specified in 

Boeing Service Bulletin 747–53–2272: At the 

applicable intervals specified in table 4 of 


tkelley on DSK3SPTVN1PROD with RULES
72576 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 

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

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014, in unrepaired 

areas, repeat the external detailed and LFEC 

inspections for cracks in the skin, and the 

external detailed and HFEC inspections for 

cracks in the external doubler, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(2) For airplanes with 15,000 or more flight 

cycles since the stringer 6 external doublers 

were installed, as specified in Boeing Service 

Bulletin 747–53–2272: At the applicable 

intervals specified in table 4 of paragraph 

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

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014, in unrepaired areas, do external 

detailed and LFEC inspections for cracks in 

the skin; and do internal and external 

detailed and HFEC inspections for cracks in 

the skin and external doubler; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(j) Repetitive Post-Modification Inspections 

for Airplane Groups 4 Through 6, and 9 

Through 11 With External Doublers Installed 

as Specified in Boeing Alert Service Bulletin 

747–53A2367 

For airplanes identified as Groups 4 

through 6, and 9 through 11, in Boeing Alert 

Service Bulletin 747–53A2367, Revision 5, 

dated July 8, 2014, with external doublers 

installed as specified in Boeing Alert Service 

Bulletin 747–53A2367: Except as provided 

by paragraph (m) of this AD, at the applicable 

time specified in table 5 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014, do internal detailed and surface 

HFEC inspections for cracks in the skin and 

internal doubler along the edge fastener rows 

of the modification, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2367, Revision 5, 

dated July 8, 2014. In unrepaired areas, 

repeat the internal detailed and surface HFEC 

inspections for cracks in the skin or internal 

doubler along the edge fastener rows of the 

modification thereafter at the applicable 

interval specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, dated July 

8, 2014. 

(k) Repetitive Post-Modification Inspections 

for Airplane Groups 12 and 13 

For airplanes identified as Groups 12 and 

13 in Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 2014: 

Except as provided by paragraph (m) of this 

AD, at the applicable time specified in table 

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

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014, do internal 

detailed and surface HFEC inspections for 

cracks in the skin and internal doubler along 

the edge fastener rows of the modification, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2367, Revision 5, dated July 8, 2014. 

In unrepaired areas, repeat the internal 

detailed and surface HFEC inspections for 

cracks in the skin or internal doubler along 

the edge fastener rows of the modification 

thereafter at the applicable interval specified 

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

Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014. 

(l) Corrective Actions 

If any cracking is found during any 

inspection required by this AD: Before 

further flight, repair the cracking using a 

method approved in accordance with the 

procedures specified in paragraph (n) of this 

AD. 

(m) Exception to Boeing Alert Service 

Bulletin 747–53A2367, Revision 5, Dated 

July 8, 2014 

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

Boeing Alert Service Bulletin 747–53A2367, 

Revision 5, dated July 8, 2014, specifies a 

compliance time ‘‘after the Revision 5 date of 

this service bulletin,’’ this AD requires 

compliance within the specified compliance 

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

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (o) 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. 

(o) Related Information 

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. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2367, Revision 5, dated July 8, 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 

November 4, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28891 Filed 11–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0927; Directorate 

Identifier 2013–NM–172–AD; Amendment 

39–18325; AD 2015–23–09] 

RIN 2120–AA64 

Airworthiness Directives; Zodiac 

Aerotechnics (Formerly Intertechnique 

Aircraft Systems) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Zodiac Aerotechnics (formerly 

Intertechnique Aircraft Systems) 

flightcrew oxygen mask regulators as 

installed on, but not limited to, various 

transport and small airplanes. This AD 

was prompted by a report that improper 

maintenance on oxygen mask regulators 

was found. This AD requires the 

identification and replacement of all 

potentially affected units. This AD also 

requires installation of a placard and 

revision of the airplane flight manual to 

include an operational procedure for 

use in case of depressurization. We are 

issuing this AD to detect and correct 

affected oxygen mask regulators, which 

could lead to inadequate protection to 

the affected flightcrew against hypoxia. 


tkelley on DSK3SPTVN1PROD with RULES