21726 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 

having P/N C16291AA after accomplishing 

the specified modification. 

(3) For airplanes on which Thales P/N 

C16291AA or P/N C16291AB AOA sensors 

are installed as of the effective date of this 

AD: No person may install, on any airplane, 

a UTAS AOA sensor having P/N 0861ED or 

P/N 0861ED2, or a SEXTANT/THOMSON 

AOA sensor having P/N 45150320, as of the 

effective date of this AD. 

(4) For airplanes on which the replacement 

required by paragraph (i) of this AD has been 

done: No person may install, on any airplane, 

a UTAS AOA sensor having P/N 0861ED or 

P/N 0861ED2, or a SEXTANT/THOMSON 

AOA sensor having P/N 45150320, after 

accomplishing the replacement. 

(5) For airplanes on which the replacement 

required by paragraph (g) of this AD has been 

done: No person may install, on any airplane, 

a UTAS AOA sensor having P/N 0861ED or 

P/N 0861ED2, or a SEXTANT/THOMSON 

AOA sensor having P/N 45150320, after 

accomplishing the replacement, except that a 

UTAS AOA sensor having P/N 0861ED may 

be installed in the standby position of that 

airplane. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0134, dated 

July 8, 2015, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–4810. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (r)(3) and (r)(4) of this AD. 

(r) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A330–34–3215, 

Revision 03, dated July 23, 2015. 

(ii) Airbus Service Bulletin A330–34–3228, 

dated October 7, 2009. 

(iii) Airbus Service Bulletin A330–34– 

3315, dated March 26, 2015. 

(iv) Airbus Service Bulletin A340–34– 

4215, Revision 03, dated July 27, 2015. 

(v) Airbus Service Bulletin A340–34–4234, 

dated October 7, 2009. 

(vi) Airbus Service Bulletin A340–34– 

4294, dated March 26, 2015. 

(vii) Airbus Service Bulletin A340–34– 

5062, Revision 02, dated July 24, 2015. 

(viii) Airbus Service Bulletin A340–34– 

5070, dated October 9, 2009. 

(ix) Airbus Service Bulletin A340–34– 

5105, dated March 26, 2015. 

(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 March 

26, 2016. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–08267 Filed 4–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2464; Directorate 

Identifier 2014–NM–195–AD; Amendment 

39–18476; AD 2016–07–31] 

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) 2013–22– 

11 for certain The Boeing Company 

Model 747–400 and –400D series 

airplanes. AD 2013–22–11 required 

repetitive inspections to detect cracks in 

the floor panel attachment fastener 

holes of certain upper deck floor beam 

upper chords, repetitive inspections, 

corrective actions if necessary, and 

replacement of the upper deck floor 

beam upper chords. Since we issued AD 

2013–22–11, we received a report that 

certain fastener holes in the upper deck 

floor beam upper chords may not have 

been inspected in accordance with AD 

2013–22–11. This AD adds additional 

repetitive inspections for cracks for 

certain airplanes, and corrective actions 

if necessary. We are issuing this AD to 

detect and correct fatigue cracking in 

certain upper chords of the upper deck 

floor beam. Such cracks could become 

large and cause the floor beams to 

become severed and result in rapid 

decompression or reduced 

controllability of the airplane. 

DATES: This AD is effective May 18, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 18, 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– 

2464. 


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Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21727 

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– 

2464; 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 

(ACO), 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 2013–22–11, 

Amendment 39–17643 (78 FR 66254, 

November 5, 2013), (‘‘AD 2013–22–11’’). 

AD 2013–22–11 applied to certain The 

Boeing Company Model 747–400 and 

–400D series airplanes. The NPRM 

published in the Federal Register on 

July 23, 2015 (80 FR 43648) (‘‘the 

NPRM’’). The NPRM was prompted by 

a report that certain fastener holes in the 

upper deck floor beam upper chords 

may not have been inspected in 

accordance with AD 2013–22–11. The 

NPRM proposed to continue to require 

repetitive inspections to detect cracks in 

the floor panel attachment fastener 

holes of certain upper deck floor beam 

upper chords, repetitive inspections, 

corrective actions if necessary, and 

replacement of the upper deck floor 

beam upper chords. The NPRM also 

proposed to require additional repetitive 

inspections for cracks for certain 

airplanes, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking in 

certain upper chords of the upper deck 

floor beam. Such cracking could become 

large and cause the floor beams to 

become severed and result in rapid 

decompression or reduced 

controllability of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. United 

Airlines supported the NPRM. 

Request To Revise ‘‘Exceptions to 

Service Information Specifications’’ 

Boeing requested that paragraph 

(m)(4), ‘‘Exceptions to Service 

Information Specifications,’’ of the 

proposed AD be revised. Boeing stated 

that Boeing Alert Service Bulletin 747– 

53A2688, Revision 1, dated September 

19, 2012, which is included in 

paragraph (m)(4), has the same 

compliance time as table 3 in Boeing 

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014; 

therefore, Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 

21, 2014, should also be included in 

paragraph (m)(4) of the proposed AD. 

For the reason provided by the 

commenter we agree to include Boeing 

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, in 

paragraph (m)(4) of this AD. We have 

also revised paragraph (m)(4) of this AD 

by removing the reference to Boeing 

Alert Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012, 

because this AD only refers to Boeing 

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, for 

compliance times. 

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 change described and minor 

editorial changes. We have determined 

that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2688, Revision 2, 

dated August 21, 2014. The service 

information describes procedures for 

upper deck floor beam upper chord 

inspection and repair at floor panel 

attachment fastener holes in section 41 

and section 42. 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 84 

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 2013–22–11).

Up to 309 work-hours × $85 

per hour = $26,265 per inspection cycle.

$0 Up to $26,265 per inspection 

cycle.

Up to $2,206,260 per inspection cycle. 

New inspections ..................... Up to 241 work-hours × $85 

per hour = $20,485.

0 Up to $20,485 per inspection 

cycle.

Up to $1,720,740 per inspection cycle. 

We have received no definitive data 

that will enable us to provide a cost 

estimate for the repair or modification 

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 


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21728 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 

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) 

2013–22–11, Amendment 39–17643 (78 

FR 66254, November 5, 2013), and 

adding the following new AD: 

2016–07–31 The Boeing Company: 

Amendment 39–18476; Docket No. 

FAA–2015–2464; Directorate Identifier 

2014–NM–195–AD. 

(a) Effective Date 

This AD is effective May 18, 2016. 

(b) Affected ADs 

This AD replaces AD 2013–22–11, 

Amendment 39–17643 (78 FR 66254, 

November 5, 2013) (‘‘AD 2013–22–11’’). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 and –400D series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 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 upper chords of the upper deck floor 

beam are subject to widespread fatigue 

damage. This AD was also prompted by 

reports that certain fastener holes in the 

upper deck floor beam upper chords in 

Section 41, may not have been inspected in 

accordance with AD 2013–22–11. We are 

issuing this AD to detect and correct fatigue 

cracking in certain upper chords of the upper 

deck floor beam, which could become large 

and cause the floor beams to become severed 

and result in rapid decompression or reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Section 41—Repetitive Inspections, and 

Corrective Actions 

At the applicable time specified in table 1 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, do open 

hole or surface high frequency eddy current 

inspections (HFEC) for cracking of the floor 

panel attachment holes in the upper deck 

floor beam upper chords, in accordance with 

Part 1 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014. If any 

crack is found during any inspection, before 

further flight, repair in accordance with Part 

2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, or repair 

using a method approved in accordance with 

the procedures specified in paragraph (o) of 

this AD. Repeat the inspections thereafter at 

the applicable time specified in table 1 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, until an 

action specified in paragraph (g)(1) or (g)(2) 

of this AD is done. 

(1) Doing a repair as a hole modification in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, Revision 2, 

dated August 21, 2014, except as required by 

paragraph (m)(2) of this AD, terminates the 

inspections required by paragraph (g) of this 

AD for the modified hole only. 

(2) Doing a modification in accordance 

with Figure 5 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 21, 

2014, except as required by paragraph (m)(2) 

of this AD, terminates the inspections 

required by paragraph (g) of this AD for the 

modification only. 

(h) Section 41—Repetitive Inspection of 

Repaired or Modified Holes, and Corrective 

Actions 

For airplanes on which a repair specified 

in Part 2 of the Accomplishment Instructions 

of Boeing Alert Service Bulletin 747– 

53A2688, Revision 2, dated August 21, 2014, 

is done, or a modification specified in Figure 

5 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, is done: 

At the applicable time specified in table 2 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, except as 

required by paragraph (m)(3) of this AD, do 

open hole or surface HFEC for cracking of 

repaired or modified floor panel attachment 

holes in the upper deck floor beam upper 

chords, in accordance with Part 1 or Part 3, 

as applicable, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 21, 

2014. If any crack is found during any 

inspection required by this paragraph, before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (o) of this AD. Repeat 

the inspections thereafter at the applicable 

time specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 2, dated 

August 21, 2014. 

(i) Section 44—Repetitive Inspection, and 

Corrective Actions 

For airplanes identified in Group 1 in 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014: At the 

applicable time specified in table 3 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, except as 

required by paragraph (m)(4) of this AD, do 

open hole or surface HFEC inspections of the 

floor panel attachment holes in the upper 

deck floor beam upper chords, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 21, 

2014. If any crack is found during any 

inspection required by this paragraph, before 

further flight, repair in accordance with Part 

5 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, except as 

required by paragraph (m)(2) of this AD. 

Repeat the inspections thereafter at the 

applicable time specified in table 3 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, until an 

action specified in paragraph (i)(1) or (i)(2) of 

this AD is done. 

(1) Doing a repair as a hole modification in 

accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, Revision 2, 

dated August 21, 2014, except as required by 

paragraph (m)(2) of this AD, terminates the 

inspections required by paragraph (i) of this 

AD for that modified hole only. 

(2) Doing a modification in accordance 

with Figure 21 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 21, 


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Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21729 

2014, except as required by paragraph (m)(2) 

of this AD, terminates the inspections 

required by paragraph (i) of this AD for that 

modified hole only. 

(j) Section 44—Repetitive Inspection of 

Repaired or Modified Holes, and Corrective 

Actions 

For airplanes identified in Group 1 in 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, on which 

a repair specified in Part 5 of Boeing Alert 

Service Bulletin 747–53A2688, Revision 2, 

dated August 21, 2014, is done or the 

modification specified in Figure 21 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, Revision 2, 

dated August 21, 2014, is done: At the 

applicable time specified in table 4 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, except as 

required by paragraph (m)(3) of this AD, do 

open hole or surface HFEC inspections of 

repaired or modified floor panel attachment 

holes in the upper deck floor beam upper 

chords, in accordance with Part 4 or Part 6, 

as applicable, of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 21, 

2014. If any crack is found during any 

inspection by this paragraph, before further 

flight, repair using a method approved in 

accordance with the procedures specified in 

paragraph (o) of this AD. Repeat the 

inspections thereafter at the applicable time 

specified in table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 2, dated 

August 21, 2014. 

(k) Sections 41 and 44—Replacement and 

Post-Replacement Repetitive Inspections 

At the applicable time specified in table 5 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014: Replace 

all upper deck floor beam upper chords, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, Revision 2, 

dated August 21, 2014. Within 20,000 flight 

cycles after doing the replacement, do the 

inspections specified in paragraphs (g) and (i) 

of this AD, as applicable. Thereafter, repeat 

the inspections required by paragraphs (g) 

and (i) of this AD, as applicable, at the times 

specified in paragraphs (g) and (i) of this AD. 

(l) Section 41—Repetitive Inspection of 

Plugged or Re-Used Holes, and Corrective 

Actions 

For airplanes identified in Group 2 in 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014: At the 

applicable time specified in table 6 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014, except as 

required by paragraph (m)(1) of this AD, at 

all plugged or reused floor panel attachment 

holes in the affected floor beam upper 

chords, do a surface HFEC inspection of the 

upper deck floor beam upper chords and 

detailed inspection for cracks on the vertical 

flange, in accordance with Part 8 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, Revision 2, 

dated August 21, 2014. If any crack is found 

during any inspection required by this 

paragraph, before further flight, repair using 

a method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD. Repeat the inspections thereafter at the 

applicable time specified in table 6 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 2, dated August 21, 2014. 

(m) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 21, 

2014, specifies a compliance time ‘‘after the 

Revision 2 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 21, 

2014; specifies to contact Boeing for certain 

procedures: Do the specified actions before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (o) of this AD. 

(3) Where table 2 or table 4 of paragraph 

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

Bulletin 747–53A2688, Revision 2, dated 

August 21, 2014, specifies to contact Boeing 

for inspections and compliance times: Before 

further flight, contact the Manager, Seattle 

Aircraft Certification Office (ACO), FAA, for 

inspections and compliance times and 

accomplish the inspections at the given 

times. 

(4) Where Boeing Alert Service Bulletin 

747–53A2688, Revision 2, dated August 21, 

2014, specifies a compliance time ‘‘after the 

Revision 1 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after December 10, 2013 

(the effective date of AD 2013–22–11). 

(n) Credit for Previous Actions 

(1) This paragraph restates the 

requirements of paragraph (o) of AD 2013– 

22–11, with new reference to paragraph (h) 

of this AD. This paragraph provides credit for 

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

of this AD, if those actions were performed 

before December 10, 2013 (the effective date 

of AD 2013–22–11), using Boeing Alert 

Service Bulletin 747–53A2688, dated August 

21, 2008, which was incorporated by 

reference in AD 2009–10–16, Amendment 

39–15901 (74 FR 22424, May 13, 2009). 

(2) This paragraph provides credit for the 

actions required by paragraphs (g) through (k) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012, which 

was incorporated by reference in AD 2013– 

22–11. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 (p) 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 2013–22–11 

are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

through (k) of this AD. 

(p) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

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

917–6590; email: Nathan.P.Weigand@

faa.gov. 

(q) 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– 

53A2688, Revision 2, dated August 21, 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; phone: 206–544– 

5000, extension 1; fax: 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on March 

30, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–08271 Filed 4–12–16; 8:45 am] 

BILLING CODE 4910–13–P 


jstallworth on DSK7TPTVN1PROD with RULES