Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 27989 

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 A330–57–3114, 

dated March 12, 2013. 

(ii) Airbus Service Bulletin A330–57–3115, 

dated April 4, 2013. 

(iii) Airbus Service Bulletin A330–57– 

3116, dated March 12, 2013. 

(iv) Airbus Service Bulletin A340–57– 

4123, dated March 12, 2013. 

(v) Airbus Service Bulletin A340–57–4124, 

Revision 01, dated August 22, 2013. 

(vi) Airbus Service Bulletin A340–57– 

4125, dated March 12, 2013. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on April 21, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10287 Filed 5–6–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0246; Directorate 

Identifier 2014–NM–187–AD; Amendment 

39–18511; AD 2016–09–13] 

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 737–300, 

–400, and –500 series airplanes. This 

AD was prompted by reports of fatigue 

cracking found at the left-side and rightside upper frames, at a certain area. This 

AD requires repetitive medium 

frequency eddy current (MFEC) 

inspections for cracking of the left-side 

and right-side upper frames, and repair 

(including open hole high frequency 

eddy current (HFEC) inspections for 

cracking of fastener holes) if necessary. 

This AD also provides an optional 

preventive modification, which 

terminates the repetitive inspections at 

the modified location. We are issuing 

this AD to detect and correct fatigue 

cracking of the upper frame, which can 

grow in size and result in a severed 

frame, leading to rapid decompression 

and consequent reduced structural 

integrity of the airplane. 

DATES: This AD is effective June 13, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 13, 2016. 

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– 

0264. 

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– 

0246; 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: 

Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: 562–627–5324; fax: 562–627– 

5210; email: galib.abumeri@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 737–300, –400, and –500 series 

airplanes. The NPRM published in the 

Federal Register on February 24, 2015 

(80 FR 9667) (‘‘the NPRM’’). The NPRM 

was prompted by reports of fatigue 

cracking found at the left-side and rightside upper frame, at a certain area. The 

NPRM proposed to require repetitive 

MFEC inspections for cracking of the 

left-side and right-side upper frames, 

and repair (including open hole HFEC 

inspections for cracking of fastener 

holes) if necessary. The NPRM also 

provided an optional preventative 

modification that would terminate the 

repetitive inspections at the modified 

location. We are issuing this AD to 

detect and correct fatigue cracking of the 

upper frame, which can grow in size 

and result in a severed frame, leading to 

rapid decompression 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 and the FAA’s 

response to each comment. 

Requests To Clarify Compliance Time 

Europe Airpost and Boeing requested 

that we revise the NPRM to clarify the 

‘‘Condition’’ column of table 1 of 

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

Alert Service Bulletin 737–53A1339, 

dated August 12, 2014, which specifies 

airplanes with certain flight cycles ‘‘on 

the original issue date of this service 

bulletin.’’ The commenters questioned 

whether the corresponding compliance 

time should be ‘‘on the effective date of 

the AD.’’ 

For the reasons suggested by both 

commenters, we agree to add paragraph 

(i)(3) to this AD to state that the 

corresponding reference point is on the 

effective date of this AD, and we have 

included reference to paragraph (i)(3) in 

all appropriate paragraphs in this AD. 

Request for Clarify Inspection 

Requirements 

Boeing requested that we revise 

paragraph (g) of the proposed AD to 

address the inspection requirements in 

areas of an existing repair to eliminate 

cracking approved by a Boeing 

Organization Designation Authorization 

(ODA) via FAA Form 8100–9. Boeing 

explained that this condition is 

addressed in note (c) of table 1 of 

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

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27990 Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 

Alert Service Bulletin 737–53A1339, 

dated August 12, 2014, and that it 

effectively terminates the initial and 

repetitive inspections required by 

paragraph (g) of the proposed AD for 

previously installed frame repairs 

approved by the Boeing ODA via FAA 

Form 8100–9. Boeing requested that the 

proposed AD address the terminating 

action for this repair condition. 

We agree that clarification is 

necessary. Boeing ODA-approved 

repairs installed prior to the effective 

date of this AD are acceptable to 

terminate the initial and repetitive 

inspections in the area under the repair. 

We have revised paragraph (g) of this 

AD accordingly, and added a new 

paragraph (g)(1) in this AD. 

Request To Clarify Required for 

Compliance (RC) Requirements 

Southwest Airlines requested that we 

clarify paragraph (l)(4) of the proposed 

AD. Southwest Airlines explained that 

note 15 in paragraph 3.A., ‘‘General 

Information,’’ of Boeing Alert Service 

Bulletin 737–53A1339, dated August 12, 

2014, states that steps in the Work 

Instructions that are identified as RC 

must be accomplished once the actions 

specified in Boeing Alert Service 

Bulletin 737–53A1339, dated August 12, 

2014, becomes mandated by an AD. 

Southwest Airlines stated that note 15 

also states that deviations to steps that 

are not identified as RC do not require 

approval of an Alternative Method of 

Compliance (AMOC). Southwest 

Airlines stated that paragraph (l)(4) of 

the proposed AD specifies that any 

service information that is identified as 

RC requires AMOC approval except as 

required by paragraph (i)(1) of the 

proposed AD. Paragraph (k) of the 

proposed AD states that the post-repair 

and post-modification inspections are 

not mandated by the AD, so it is unclear 

whether the proposed AD would require 

the operator to contact Boeing if there 

are crack findings during the post-repair 

and post-modification inspections, and 

whether or not the resulting repairs are 

subject to the requirements of the AD. 

We agree to provide clarification. 

Paragraph (k) of this AD states that the 

post-repair and post-modification 

inspections specified in tables 4 and 5 

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

Boeing Alert Service Bulletin 737– 

53A1339, dated August 12, 2014, are not 

required by this AD (tables 4 and 5 

correspond to Parts 6 and 7, 

respectively, of the service 

information.). The RC steps in those 

parts are also not required by this AD. 

Any cracking found—whether during 

accomplishment of the actions required 

by an AD or during routine 

maintenance—is required by 14 CFR 

43.13(b) to be repaired before further 

flight. However, for clarity, we have 

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

refer only to Part 3 and Part 4 of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1339, 

dated August 12, 2014. In addition, we 

have revised paragraph (l)(4) of this AD 

to refer to Part 2, Part 3, and Part 4 of 

the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737– 

53A1339, dated August 12, 2014. 

Request To Address Repairs for 

Damage Other Than Cracking 

Southwest Airlines stated that the 

NPRM does not specifically address 

existing repairs that prevent 

accomplishment of the inspections 

proposed in paragraph (g) of the 

proposed AD. Note (c) in table 1 of 

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

Alert Service Bulletin 737–53A1339, 

dated August 12, 2014, specifies that an 

ODA-approved repair, via FAA Form 

8100–9, installed to eliminate 

previously found cracking, eliminates 

the need for the repetitive inspections at 

the repaired locations. Southwest 

requested that we revise the NPRM to 

apply this provision to repairs for 

damage other than cracking. Southwest 

Airlines also requested that we 

specifically state that any repair 

approved by Boeing via an FAA 8100– 

9 combined with approval of an AMOC 

to paragraph (h) of the proposed AD 

terminates both the initial and repetitive 

inspections required by paragraph (g) of 

the proposed AD. 

We agree to add clarification 

regarding initial and repetitive 

inspections. To provide additional 

clarification in the rule we have revised 

the wording in paragraphs (g) and (h) of 

this AD. Also, we agree to revise the 

NPRM to include in this final rule, the 

provision for repairs for cracking in 

paragraph (g)(1) of this AD, and the 

provision for repairs that were installed 

for damage other than cracking that 

have been re-evaluated and approved by 

the Boeing ODA with an FAA Form 

8100–9 combined with an AMOC 

statement, in paragraph (g)(2) of this 

AD. 

Effect of Winglets on the 

Accomplishment of the Proposed 

Actions 

Aviation Partners Boeing stated that 

accomplishing Supplemental Type 

Certificate (STC) ST01219SE (http://rgl.

faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/ebd1cec7b301293e

86257cb30045557a/$FILE/

ST01219SE.pdf) does not affect the 

actions specified in the NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) in this 

AD, and have added new paragraph 

(c)(2) to this AD to state that installation 

of STC ST01219SE does not affect the 

ability to accomplish the actions 

required by this final rule. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ AMOC 

approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

Change to Paragraph (k) of This AD 

We have revised paragraph (k) of this 

AD to clarify that the post-modification 

inspections are airworthiness 

limitations that are required by 

maintenance and operational rules; 

therefore, these inspections are not 

required by this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Boeing has issued Boeing Alert 

Service Bulletin 737–53A1339, dated 

August 12, 2014. The service 

information describes procedures for 

repetitive MFEC inspections for 

cracking, repair the cracking including 

doing an open hole HFEC inspections 

for cracking of the holes, and an 

optional modification of an inspection 

area including open hole and surface 

HFEC inspections for cracking of the 

area to be modified. 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 109 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

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Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 27991 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections .................... 14 work-hours × $85 per hour = $1,190 per inspection cycle.$0 $1,190 per inspection 

cycle.

$129,710 per inspection 

cycle. 

Preventive modification 

(optional).

15 work-hours × $85 per hour = $1,275 ............ 0 $1,275 .......................... $138,975. 

We estimate the following costs to do 

any necessary on-condition 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 

Repair and open hole HFEC inspection ... 36 work-hours × $85 per hour = $3,060 .......................................... $0 $3,060 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–09–13 The Boeing Company: 

Amendment 39–18511; Docket No. 

FAA–2015–0246; Directorate Identifier 

2014–NM–187–AD. 

(a) Effective Date 

This AD is effective June 13, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–300, –400, and –500 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

737–53A1339, dated August 12, 2014. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://rgl.faa.

gov/Regulatory_and_Guidance_Library/

rgstc.nsf/0/ebd1cec7b301293e86257cb30

045557a/$FILE/ST01219SE.pdf) does not 

affect the ability to accomplish the actions 

required by this AD. Therefore, for airplanes 

on which STC ST01219SE is installed, a 

‘‘change in product’’ alternative method of 

compliance (AMOC) approval request is not 

necessary to comply with the requirements of 

14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53: Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking found at the left-side and 

right-side upper frames, at station 360 

between stringer 13 and stringer 14. We are 

issuing this AD to detect and correct fatigue 

cracking of the upper frame, which can grow 

in size and result in a severed frame, leading 

to rapid decompression and consequent 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections for Cracking 

Except as required by paragraphs (i)(2) and 

(i)(3) of this AD: At the applicable times 

specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1339, dated August 12, 

2014, do a medium frequency eddy current 

(MFEC) inspection for cracking on the leftside and right-side of the upper frame at 

station 360 between stringer 13 and stringer 

14, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1339, dated August 

12, 2014. If no cracking is found, repeat the 

inspections at the applicable times specified 

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

of Boeing Alert Service Bulletin 737– 

53A1339, dated August 12, 2014. 

Accomplishment of the actions specified in 

paragraph (j) of this AD terminates the 

repetitive inspections required by this 

paragraph at the modified area only. The 

initial and repetitive inspections required by 

this paragraph may be terminated in the area 

under repairs installed prior to the effective 

date of this AD, provided they meet the 

requirements of paragraph (g)(1) or (g)(2) of 

this AD. 

(1) Repairs were installed to eliminate 

previously found cracking and were 

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27992 Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 

approved by the Boeing Organization 

Designation Authorization (ODA) with an 

FAA Form 8100–9. 

(2) Repairs were installed for damage other 

than cracking that have been re-evaluated 

and approved by the Boeing ODA with an 

FAA Form 8100–9 that includes an 

alternative method of compliance (AMOC) 

statement to paragraph (h) of this AD. 

(h) Repair 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD: Before further flight, repair the cracking 

including doing an open hole high frequency 

eddy current (HFEC) inspection for cracking 

of the holes, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1339, dated August 

12, 2014, except as required by paragraph 

(i)(1) of this AD. Repair of any crack 

terminates the initial and repetitive 

inspection requirements of paragraph (g) of 

this AD for the repaired area only. If any 

cracking 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 (l) of this AD. 

(i) Exceptions to Service Information 

Specifications 

(1) Where Part 3 and Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1339, dated August 

12, 2014, specifies contacting Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(2) Where Boeing Alert Service Bulletin 

737–53A1339, dated August 12, 2014, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified time after the effective date of this 

AD. 

(3) Where the Condition column of table 1 

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

Alert Service Bulletin 737–53A1339, dated 

August 12, 2014, specifies a reference point 

‘‘on the original issue date of this service 

bulletin,’’ for this AD the corresponding 

reference point is on the effective date of this 

AD. 

(j) Optional Preventive Modification 

Modification of an inspection area 

specified in paragraph (g) of this AD, 

including open hole and surface HFEC 

inspections for cracking of the area to be 

modified, in accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1339, dated August 

12, 2014, except as required by paragraph 

(i)(1) of this AD, terminates the repetitive 

inspections required by paragraph (g) of this 

AD at the modified location only. 

(k) Post-Repair and Post-Modification 

Inspections 

Tables 4 and 5 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1339, dated August 12, 

2014, specify post-modification 

airworthiness limitation inspections in 

compliance to 14 CFR 25.571(a)(3) at the 

modified locations, which support 

compliance with 14 CFR 121.1109(c)(2) or 

129.109(b)(2). As airworthiness limitations, 

these inspections are required by 

maintenance and operational rules. It is 

therefore unnecessary to mandate them in 

this AD. Deviations from these inspections 

require FAA approval, but do not require an 

alternative method of compliance. 

(l) 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 (m) 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 

Boeing Commercial Airplanes 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) Except as required by paragraph (i)(1) 

of this AD: Where Part 2, Part 3, and Part 4 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1339, 

dated August 12, 2014, contains steps that 

are labeled as RC, the provisions of 

paragraphs (l)(4)(i) and (l)(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. 

(m) Related Information 

For more information about this AD, 

contact Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: 562–627– 

5324; fax: 562–627–5210; email: 

galib.abumeri@faa.gov. 

(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 737– 

53A1339, dated August 12, 2014. 

(ii) Reserved. 

(3) For Boeing 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/ibr-locations.html. 

Issued in Renton, Washington, on April 28, 

2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10524 Filed 5–6–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Parts 97 and 160 

46 CFR Part 97 

[Docket No. USCG–2000–7080] 

RIN 1625–AA25 [Formerly RIN 2115–AF97] 

Cargo Securing Manuals 

AGENCY: Coast Guard, DHS. 

ACTION: Interim rule and request for 

comment. 

SUMMARY: The Coast Guard is issuing an 

interim rule to require U.S. and foreign 

self-propelled cargo vessels of 500 gross 

tons or more, traveling on international 

voyages and carrying cargo that is other 

than solid or liquid bulk cargo, to have 

cargo securing manuals (CSMs) on 

board. The rule also requires those 

vessels to comply with certain 

provisions of the International 

Convention for the Safety of Life at Sea, 

1974 as amended (SOLAS), authorizes 

recognized classification societies or 

other approval authorities to review and 

approve CSMs on behalf of the Coast 

Guard; and prescribes when and how 

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