Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43475 

A300–57–6115, dated April 4, 2014, refers to 

Structural Repair Manual (SRM) 51–40–13 

for applying special protection, the correct 

reference is SRM 51–23–20; and to SRM 51– 

40–12 for applying paint coatings, the correct 

reference is SRM 51–23–10. 

(h) Repetitive Rototest Inspections 

Within 36 months after the effective date 

of this AD: Remove the fasteners and 

measure the diameter of the fastener holes; 

and, before further flight, do the applicable 

actions required by paragraph (h)(1) or (h)(2) 

of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0257, excluding 

Appendix 01 and including Appendix 02, 

dated April 4, 2014 (for Model A300 B2–1A, 

B2–1C, B2K–3C, B2–203, B4–2C, B4–103, 

and B4–203 airplanes); or Airbus Service 

Bulletin A300–57–6115, dated April 4, 2014 

(for Model A300 B4–601, B4–603, B4–620, 

B4–622, B4–605R, B4–622R, F4–605R, F4– 

622R, and C4–605R Variant F airplanes). 

(1) If one or more of the hole diameters is 

outside the tolerance of the nominal 

diameter, and outside the tolerance of the 

first and second oversize: Do the applicable 

corrective actions required by paragraph (i) of 

this AD. 

(2) If all of the hole diameters are within 

the tolerance of the nominal diameter or the 

first or second oversize: Do detailed and 

rototest inspections for cracking of the 

fastener holes at the left-hand and right-hand 

sides of the FR40 lower junction, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–0257, excluding Appendix 01 and 

including Appendix 02, dated April 4, 2014 

(for Model A300 B2–1A, B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes); or Airbus Service Bulletin A300– 

57–6115, dated April 4, 2014 (for Model 

A300 B4–601, B4–603, B4–620, B4–622, B4– 

605R, B4–622R, F4–605R, F4–622R, and C4– 

605R Variant F airplanes). If no cracking is 

found, before further flight, install new 

fasteners of the same diameter in special 

clearance fit for fasteners 1 through 3 of the 

FR40 lower junction, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletins A300–57–0257, excluding 

Appendix 01 and including Appendix 02, 

dated April 4, 2014; or Airbus Service 

Bulletin A300–57–6115, dated April 4, 2014. 

Repeat the rototest inspection thereafter at 

intervals not to exceed 7,000 flight cycles. 

Accomplishment of a rototest inspection 

required by this paragraph terminates the 

repetitive HFEC inspections required by 

paragraph (g) of this AD. 

(i) Corrective Actions 

If, during any inspection required by this 

AD, any crack is found, or one or more of the 

hole diameters is outside the tolerance of the 

nominal diameter, and outside the tolerance 

of the first and second oversize: Repair before 

further flight in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

(j) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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): Except 

as required by paragraph (i) of this AD: 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. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0272, dated 

December 12, 2014, 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–2015–8134. 

(l) 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 A300–57–0257, 

excluding Appendix 01 and including 

Appendix 02, dated April 4, 2014. 

(ii) Airbus Service Bulletin A300–57–6115, 

dated April 4, 2014. 

(3) For Airbus service information 

identified in this final rule, contact Airbus 

SAS, Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 96; 

fax +33 5 61 93 44 51; email 

account.airworth-eas@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 June 21, 

2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–15356 Filed 7–1–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8131; Directorate 

Identifier 2015–NM–073–AD; Amendment 

39–18575; AD 2016–13–11] 

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) 2008–05– 

06 for certain The Boeing Company 

Model 737–100, –200, –300, –400, and 

–500 series airplanes. AD 2008–05–06 

required repetitive inspections for 

fatigue cracking in the longitudinal floor 

beam web, upper chord, and lower 

chord located at certain body stations, 

and repair if necessary. This new AD 

requires, for certain airplanes, an 

inspection to determine if tapered fillers 

are installed, and related investigative 

and corrective actions if necessary. This 

AD was prompted by reports of cracks 

in the center wing box longitudinal floor 

beams, upper chord, and lower chord. 

We are issuing this AD to detect and 

correct fatigue cracking of the upper and 

lower chords and web of the 

longitudinal floor beams, which could 

result in rapid loss of cabin pressure. 


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43476 Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 

DATES: This AD is effective August 9, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 9, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of April 8, 2008 (73 FR 

11538, March 4, 2008). 

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– 

8131. 

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– 

8131; 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, CA 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 to supersede AD 2008–05–06, 

Amendment 39–15400 (73 FR 11538, 

March 4, 2008) (‘‘AD 2008–05–06’’). AD 

2008–05–06 applied to certain The 

Boeing Company Model 737–100, –200, 

–300, –400, and –500 series airplanes. 

The NPRM published in the Federal 

Register on January 12, 2016 (81 FR 

1345) (‘‘the NPRM’’). The NPRM was 

prompted by reports of cracks in the 

center wing box longitudinal floor 

beams, upper chord, and lower chord. 

The NPRM proposed to continue to 

require repetitive inspections for fatigue 

cracking in the longitudinal floor beam 

web, upper chord, and lower chord 

located at certain body stations, and 

repair if necessary. The NPRM also 

proposed to require, for certain 

airplanes, an inspection to determine if 

tapered fillers are installed, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking of the 

upper and lower chords and web of the 

longitudinal floor beams, which could 

result in rapid loss of cabin pressure. 

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. 

Support for the NPRM 

Boeing stated that it has reviewed the 

NPRM and concurs with the contents. 

Ms. Kathleen Whitworth stated that 

the NPRM is a good idea because the 

safety of airline passengers outweighs 

the extra cost of the added inspection 

and that she is in full support of the 

NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/

$FILE/ST01219SE.pdf) does not affect 

accomplishment of the actions specified 

in the NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) and 

added a new paragraph (c)(2) to this AD 

to state that installation of STC 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/

$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. 

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 

We reviewed Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, 

dated April 1, 2015. The service 

information describes procedures for 

various inspections for fatigue cracks in 

the longitudinal floor beam web, upper 

chord, and lower chord, located at the 

applicable body stations, repairs 

(including related investigative and 

corrective actions), and preventive 

modifications (including related 

investigative and corrective actions) that 

terminate the repetitive inspections. The 

service information also describes 

procedures for an inspection to 

determine if tapered fillers are installed, 

and related investigative 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 652 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43477 

ESTIMATED COSTS

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

operators 

Inspections [retained actions from AD 

2008–05–06].

Up to 25 work-hours × $85 per hour = 

$2,125 per inspection cycle.

$0 $2,125 per inspection cycle.$1,385,500 per inspection cycle. 

Tapered filler inspection [new action] .... 4 work-hours × $85 per hour = $340 ..... $0 $340 ....................... $221,680. 

We estimate the following costs to do 

any necessary repairs 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 repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Floor beam repair and optional preventative modification.Up to 198 work-hours × $85 per hour = $16,830 ...... (1) Up to $16,830 

Tapered filler repair ..................................................... 174 work-hours × $85 per hour = $14,790 ................ (1) $14,790 

1We have received no definitive data that would enable us to provide parts cost estimates for the 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) 

2008–05–06, Amendment 39–15400 (73 

FR 11538, March 4, 2008), and adding 

the following new AD: 

2016–13–11 The Boeing Company: 

Amendment 39–18575; Docket No. 

FAA–2015–8131; Directorate Identifier 

2015–NM–073–AD. 

(a) Effective Date 

This AD is effective August 9, 2016. 

(b) Affected ADs 

This AD replaces AD 2008–05–06, 

Amendment 39–15400 (73 FR 11538, March 

4, 2008) (‘‘AD 2008–05–06’’). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–100, –200, –300, –400, 

and –500 series airplanes; certificated in any 

category; as identified in Boeing Alert 

Service Bulletin 737–57A1296, Revision 2, 

dated April 1, 2015. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/$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 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in the center wing box longitudinal floor 

beams, upper chord, and lower chord. We are 

issuing this AD to detect and correct fatigue 

cracking of the upper and lower chords and 

web of the longitudinal floor beams, which 

could result in rapid loss of cabin pressure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections, With Revised 

Service Information and Revised Affected 

Airplanes 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–05–06, with revised 

service information and revised affected 

airplanes. For Groups 1 through 4 airplanes 

identified in Boeing Alert Service Bulletin 

737–57A1296, Revision 2, dated April 1, 

2015, do the various inspections for fatigue 

cracks in the longitudinal floor beam web, 

upper chord, and lower chord, located at the 

applicable body stations specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–57–1296, dated June 13, 

2007; or Boeing Alert Service Bulletin 737– 

57A1296, Revision 2, dated April 1, 2015; by 

doing all the actions in accordance with the 

Accomplishment Instructions of Boeing 


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Service Bulletin 737–57A1296, dated June 

13, 2007; or Boeing Alert Service Bulletin 

737–57A1296, Revision 2, dated April 1, 

2015; except as provided by paragraph (h) of 

this AD. Do the inspections at the time 

specified in paragraph (g)(1) or (g)(2) of this 

AD, as applicable. As of the effective date of 

this AD, only use Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, dated 

April 1, 2015, for accomplishing the actions 

required by this paragraph. 

Note 1 to paragraphs (g) and (h) of this 

AD: The airplane groups identified in Boeing 

Service Bulletin 737–57–1296, dated June 13, 

2007, do not, in all cases, match the airplane 

groups identified in Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, dated 

April 1, 2015 (Group 4 airplanes in Boeing 

Alert Service Bulletin 737–57A1296, 

Revision 2, dated April 1, 2015, coincide 

with certain Group 2 airplanes in Boeing 

Service Bulletin 737–57–1296, dated June 13, 

2007). 

(1) For Groups 1 and 2 airplanes, except for 

line numbers 1 through 291, identified in 

Boeing Service Bulletin 737–57–1296, dated 

June 13, 2007: Do the inspections at the 

applicable initial compliance time listed in 

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

Service Bulletin 737–57–1296, dated June 13, 

2007, except where Boeing Service Bulletin 

737–57–1296, dated June 13, 2007, specifies 

a compliance time after the date on the 

service bulletin, this AD requires compliance 

within the specified compliance time after 

April 8, 2008 (the effective date of AD 2008– 

05–06). Repeat the inspections thereafter at 

the intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–57–1296, dated June 13, 2007. 

(2) For Group 3 airplanes identified in 

Boeing Service Bulletin 737–57–1296, dated 

June 13, 2007: Do the inspections at the 

applicable initial compliance time listed in 

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

Service Bulletin 737–57–1296, dated June 13, 

2007, except where Boeing Service Bulletin 

737–57–1296, dated June 13, 2007, specifies 

a compliance time after the date on the 

service bulletin, this AD requires compliance 

within the specified compliance time after 

April 8, 2008 (the effective date of AD 2008– 

05–06). Repeat the inspections thereafter at 

the intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–57–1296, dated June 13, 2007. 

(h) Retained Repair Instructions, With 

Revised Service Information That Contains 

New Repair Actions 

This paragraph restates the requirements of 

paragraph (g) of AD 2008–05–06, with 

revised service information that contains new 

repair actions. If any crack is found during 

any inspection required by paragraph (g) of 

this AD, do the applicable actions specified 

in paragraph (h)(1) or (h)(2) of this AD. 

(1) For inspections done using Boeing 

Service Bulletin 737–57–1296, dated June 13, 

2007: If any crack is found during any 

inspection required by paragraph (g) of this 

AD, and Boeing Service Bulletin 737–57– 

1296, dated June 13, 2007, specifies 

contacting Boeing for repair instructions, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. 

(2) For inspections done using Boeing Alert 

Service Bulletin 737–57A1296, Revision 2, 

dated April 1, 2015: If any crack is found 

during any inspection required by paragraph 

(g) of this AD, before further flight, repair, 

including doing all applicable related 

investigative actions and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1296, Revision 2, dated April 1, 

2015; except where Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, dated 

April 1, 2015, specifies contacting Boeing for 

repair instructions, before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. Accomplishing a 

repair specified in Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, dated 

April 1, 2015, terminates the repetitive 

inspections required by paragraph (g) of this 

AD for the repaired area only. 

(i) New Requirement of This AD: Inspection 

for Tapered Fillers for Certain Airplanes, 

Related Investigative Actions, and 

Corrective Actions 

For Groups 1 through 4, Configuration 1 

airplanes identified in Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, dated 

April 1, 2015: Except as provided by 

paragraph (k) of this AD, at the applicable 

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

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, dated 

April 1, 2015, do an inspection to determine 

if tapered fillers are installed; and do all 

applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–57A1296, Revision 2, 

dated April 1, 2015; except where Boeing 

Alert Service Bulletin 737–57A1296, 

Revision 2, dated April 1, 2015, specifies 

contacting Boeing for repair instructions, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. A 

review of the maintenance records is 

acceptable in lieu of this inspection if the 

installation of tapered fillers can be 

conclusively determined from that review. 

(j) New Requirement of This AD: Inspections 

and Corrective Actions for Group 5 

Airplanes 

For Group 5 airplanes identified in Boeing 

Alert Service Bulletin 737–57A1296, 

Revision 2, dated April 1, 2015: Except as 

provided by paragraph (k) of this AD, at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, dated 

April 1, 2015; accomplish inspections and 

applicable corrective actions using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. 

(k) Exception to Service Information 

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

Boeing Alert Service Bulletin 737–57A1296, 

Revision 2, dated April 1, 2015, 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.’’ 

(l) Optional Terminating Action 

Accomplishing the applicable preventative 

modification specified in paragraph 3.B.4., 

‘‘Preventive Modification’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–57A1296, Revision 2, 

dated April 1, 2015, terminates the 

applicable repetitive inspection required by 

paragraph (g) of this AD. The preventative 

modification, including related investigative 

and corrective actions, must be done in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1296, Revision 2, dated April 1, 

2015; except where Boeing Alert Service 

Bulletin 737–57A1296, Revision 2, dated 

April 1, 2015, specifies contacting Boeing for 

repair instructions, before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Service Bulletin 737–57–1296, Revision 1, 

dated September 26, 2012. This document is 

not incorporated by reference in this AD. 

(n) 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 (o)(1) 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, 

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, Los Angeles 

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 as specified in the 

fourth paragraph (related to AD 2008–05–06) 

of Section 1.F., Approval, of Boeing Service 

Bulletin 737–57–1296, Revision 1, dated 

September 26, 2012, for repairs and 

modifications are not approved for any 

provision of this AD. All other AMOCs 

approved for AD 2008–05–06 are approved as 

AMOCs for the corresponding provisions of 

this AD. 


sradovich on DSK3GDR082PROD with RULES
Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 43479 

(o) Related Information 

(1) 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, CA 

90712–4137; phone: 562–627–5324; fax: 562– 

627–5210; email: galib.abumeri@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(5) and (p)(6) of this AD. 

(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. 

(3) The following service information was 

approved for IBR on August 9, 2016. 

(i) Boeing Alert Service Bulletin 737– 

57A1296, Revision 2, dated April 1, 2015. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on April 8, 2008 (73 FR 

11538, March 4, 2008). 

(i) Boeing Service Bulletin 737–57–1296, 

dated June 13, 2007. 

(ii) Reserved. 

(5) 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. 

(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 June 21, 

2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–15355 Filed 7–1–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–8032; Directorate 

Identifier 2016–SW–037–AD; Amendment 

39–18578; AD 2016–12–51] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are publishing a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS332L2 and Model 

EC225LP helicopters, which was sent 

previously to all known U.S. owners 

and operators of these helicopters. This 

AD immediately prohibits flight of all 

Model AS332L2 and EC225LP 

helicopters. This AD is prompted by an 

accident involving an EC225LP 

helicopter in which the main rotor hub 

(MRH) detached from the main gearbox 

(MGB). These actions are intended to 

prevent failure of the main rotor system 

and subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective July 

20, 2016 to all persons except those 

persons to whom it was made 

immediately effective by Emergency AD 

2016–12–51, issued on June 3, 2016, 

which contains the requirements of this 

AD. 

We must receive comments on this 

AD by September 6, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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–2016– 

8032; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the European Aviation 

Safety Agency (EASA) AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110, email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

On June 3, 2016, we issued 

Emergency AD 2016–12–51 to correct an 

unsafe condition for Model AS332L2 

and EC225LP helicopters. Emergency 

AD 2016–12–51 immediately prohibits 

further flight of Model AS332L2 and 

EC225LP helicopters. The emergency 

AD was sent previously to all known 

U.S. owners and operators of these 

helicopters. 

Emergency AD 2016–12–51 was 

prompted by Emergency AD No. 2016– 

0104–E, dated June 2, 2016, issued by 

EASA, which is the Technical Agent for 

the Member States of the European 


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