Federal Register / Vol. 82, No. 37 / Monday, February 27, 2017 / Rules and Regulations 11797 

FAA–2016–9053; Directorate Identifier 

2016–NM–075–AD. 

(a) Effective Date 

This AD is effective April 3, 2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 747–8 and 747–8F series 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of 

damaged vapor seals, block seals, and heat 

shield seals on the outboard pylons between 

the engine strut and aft fairing. We are 

issuing this AD to detect and correct heat 

damage to the vapor seals between the engine 

strut and aft fairing. Such damage could 

allow flammable fluid leakage out of the aft 

fairing, which could result in an 

uncontrolled fire in the engine strut. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: Do a 

detailed inspection for heat damage of the 

vapor seals on the outboard pylons between 

the strut and aft fairing of the numbers 1 and 

4 engines, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2246, dated 

February 5, 2016. Repeat the inspection 

thereafter at intervals not to exceed 1,200 

flight cycles. 

(1) Before the accumulation of 1,800 total 

flight cycles, or within 1,800 flight cycles 

after the most recent vapor seal, block seal, 

and heat shield seal replacement, whichever 

is later. 

(2) Within 6 months after the effective date 

of this AD. 

(h) Replacement 

If during any inspection required by 

paragraph (g) of this AD any heat damage of 

any vapor seal is found: Before further flight, 

replace the vapor seal, heat shield seal, and 

block seal with new seals, in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–54A2246, 

dated February 5, 2016. Repeat the 

inspection required by paragraph (g) of this 

AD within 1,800 flight cycles after doing the 

replacement, and thereafter at intervals not to 

exceed 1,200 flight cycles. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j) 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) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) 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. 

(j) Related Information 

For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6505; fax: 425– 

917–6590; email: tung.tran@faa.gov. 

(k) 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– 

54A2246, dated February 5, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; 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/ibrlocations.html. 

Issued in Renton, Washington, on February 

10, 2017. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2017–03362 Filed 2–24–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3984; Directorate 

Identifier 2015–NM–033–AD; Amendment 

39–18803; AD 2017–04–08] 

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) 2008–13– 

12 R1 for certain The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. AD 

2008–13–12 R1 required various 

repetitive inspections for cracking of a 

certain splice of the fuselage, and other 

specified and corrective actions if 

necessary; and provided for an optional 

preventive modification, which 

terminated the repetitive inspections. 

This new AD adds an inspection to 

determine if the existing frame repair 

meets all specified requirements; a 

modification of a certain splice, which 

terminates the repetitive inspections; 

reduces certain inspection thresholds 

and repetitive intervals; and adds postrepair/post-modification inspections. 

This AD was prompted by reports of 

additional fatigue cracking of a certain 

splice of the fuselage and one report of 

a severed frame, due to susceptibility to 

widespread fatigue damage (WFD). We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective April 3, 

2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 3, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 


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Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 

110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; 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– 

3984. 

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– 

3984; 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 supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to supersede AD 

2008–13–12 R1, Amendment 39–15719 

(73 FR 67383, November 14, 2008) (‘‘AD 

2008–13–12 R1’’). AD 2008–13–12 R1 

applied to certain The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. The 

SNPRM published in the Federal 

Register on November 14, 2016 (81 FR 

79395). We preceded the SNPRM with 

a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on October 9, 2015 (80 FR 

61133). The NPRM proposed to 

continue to require the actions of AD 

2008–13–12 R1. The NPRM also 

proposed to add, for certain airplanes, 

an inspection to determine if the 

existing frame repair meets all specified 

requirements, and for certain other 

airplanes, a new modification of the 

upper-frame-to-side-frame splice, which 

would terminate the repetitive 

inspections. The NPRM also proposed 

to reduce certain inspection thresholds 

and repetitive intervals. The NPRM was 

prompted by reports of additional 

fatigue cracking of the upper-frame-toside-frame splice of the fuselage, and 

one report of a severed frame. The 

SNPRM proposed to add post-repair/ 

post-modification inspections that were 

not included in the NPRM. We are 

issuing this AD to detect and correct 

fatigue cracking of the upper-frame-toside-frame splice of the fuselage, which 

could result in reduced structural 

integrity of the frame and adjacent lap 

joint, causing increased loading in the 

fuselage skin, which will accelerate skin 

crack growth and could result in 

decompression of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The commenter, Stephanie Reid, agreed 

that the airplanes should be inspected. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–53A1261, Revision 1, 

dated January 30, 2015. The service 

information describes procedures for 

various repetitive inspections for 

cracking of the upper-frame-to-sideframe splice of the fuselage, a 

preventive modification to prevent 

WFD, an inspection to determine if the 

existing frame repair meets all specified 

requirements, 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 391 

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 

Retained inspections 

from AD 2008–13–12 

R1.

Between 18 and 38 work-hours × $85 per hour, 

depending on airplane configuration = between $1,530 and $3,230 per inspection 

cycle.

$0 Between $1,530 and 

$3,230 per inspection 

cycle.

Between $598,230 and 

$1,262,930, per inspection cycle. 

New inspections ............ 213 work-hours × $85 per hour, $18,105 per inspection cycle.$0 $18,105 per inspection 

cycle.

Up to $7,079,055, per 

inspection cycle. 

New modification ........... 256 work-hours × $85 per hour = $21,760 ........ (1) $21,760 ........................ Up to $8,508,160. 

1We currently have no specific cost estimates associated with the parts necessary for the modification. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 


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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) 

2008–13–12 R1, Amendment 39–15719 

(73 FR 67383, November 14, 2008), and 

adding the following new AD: 

2017–04–08 The Boeing Company: 

Amendment 39–18803; Docket No. 

FAA–2015–3984; Directorate Identifier 

2015–NM–033–AD. 

(a) Effective Date 

This AD is effective April 3, 2017. 

(b) Affected ADs 

This AD replaces AD 2008–13–12 R1, 

Amendment 39–15719 (73 FR 67383, 

November 14, 2008) (‘‘AD 2008–13–12 R1’’). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–100, –200, –200C, 

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

certificated in any category, as identified in 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/BE866B732F6CF31086257

B9700692796?OpenDocument&Highlight=

st01219se) 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 

additional fatigue cracking of the upperframe-to-side-frame splice of the fuselage, 

and one report of a severed frame due to 

susceptibility to widespread fatigue damage 

(WFD). We are issuing this AD to detect and 

correct fatigue cracking of the upper-frameto-side-frame splice of the fuselage, which 

could result in reduced structural integrity of 

the frame and adjacent lap joint, causing 

increased loading in the fuselage skin, which 

will accelerate skin crack growth and could 

result in decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Corrective 

Actions for Certain Airplanes 

(1) For Groups 1 through 3, Configurations 

1, 3, 4, and 5 airplanes; Group 7, 

Configurations 1, 3, 4, and 5 airplanes; 

Groups 4 through 6, Configurations 1, 3, 4, 

and 6 airplanes; and Groups 8 through 11, 

Configurations 1, 3, 4, and 6 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Do the actions specified in paragraphs 

(g)(1)(i) and (g)(1)(ii) of this AD, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD. Do all 

applicable corrective actions before further 

flight. 

(i) At the applicable time specified in 

Tables 1, 2, 3, 5, 6, and 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1261, Revision 1, dated 

January 30, 2015, except as required by 

paragraphs (i)(1) and (i)(2) of this AD: Do 

medium frequency eddy current inspections 

for cracking of the upper-frame-to-side-frame 

splice of the fuselage. 

(ii) Repeat the inspections specified in 

paragraph (g)(1)(i) of this AD at the 

applicable time specified in Tables 1, 2, 3, 5, 

6, and 8 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, until the 

preventive modification required by 

paragraph (k) of this AD, or a terminating 

action specified in paragraph (l) of this AD, 

has been accomplished. The inspections are 

terminated for the repaired or modified areas 

only. 

(2) For Groups 4 through 6, Configurations 

2 and 5 airplanes; and Groups 8 through 11, 

Configurations 2 and 5 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Do the actions specified in paragraphs 

(g)(2)(i) and (g)(2)(ii) of this AD, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD. Do all 

applicable corrective actions before further 

flight. 

(i) At the applicable time specified in 

Tables 4 and 7 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1261, Revision 1, dated 

January 30, 2015, except as required by 

paragraphs (i)(1) and (i)(2) of this AD: Do a 

detailed inspection to determine if the 

existing frame repair meets all requirements 

specified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015, and for any frame repair that does meet 

all requirements, do detailed and high 

frequency eddy current (HFEC) inspections 

for cracking of the existing frame repairs. 

(ii) Repeat the inspections for cracking 

specified in paragraph (g)(2)(i) of this AD at 

the applicable time specified in Tables 4 and 

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

Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015. 

(h) Post-Repair and Post-Modification 

Actions for Certain Airplanes 

For Group 1, Configurations 2 and 6 

airplanes; Group 2, Configurations 2 and 6 

airplanes; Group 3, Configurations 2 and 6 

airplanes; and Group 7, Configurations 2 and 

6 airplanes; as identified in Boeing Alert 

Service Bulletin 737–53A1261, Revision 1, 

dated January 30, 2015: Within 120 days after 

the effective date of this AD, do post-repair 

and post-modification actions using a 

method approved in accordance with the 

procedures specified in paragraph (n) of this 

AD. 

(i) Exceptions to Service Bulletin 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015, specifies a compliance time ‘‘after the 

Revision 1 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where the ‘‘Condition’’ column of 

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

Alert Service Bulletin 737–53A1261, 


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Revision 1, dated January 30, 2015, specifies 

a condition based on whether an airplane has 

or has not been inspected, this AD bases the 

condition on whether an airplane has or has 

not been inspected as of the effective date of 

this AD. 

(3) Where Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015, specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (n) of 

this AD. 

(j) Post-Repair and Post-Modification 

Inspections 

For Groups 4 through 6, Configurations 1, 

3, 4, 6, 7, 8, 9, and 10 airplanes; and Groups 

8 through 11, Configurations 1, 3, 4, 6, 7, 8, 

9, and 10 airplanes; as identified in Boeing 

Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015: Except as 

provided by paragraphs (i)(1) and (i)(2) of 

this AD, at the applicable time specified in 

Tables 12 through 17 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1261, Revision 1, dated 

January 30, 2015; do the post-repair/postmodification inspections, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD. Do all 

applicable corrective actions before further 

flight. 

(k) Preventive Modification for Certain 

Airplanes 

For Groups 4 through 6, Configurations 1, 

3, 4, and 6 airplanes; and Groups 8 through 

11, Configurations 1, 3, 4, and 6 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Except as provided by paragraphs (i)(1) 

and (i)(2) of this AD, at the applicable time 

specified in Tables 3, 5, 6, and 8 in paragraph 

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

Bulletin 737–53A1261, Revision 1, dated 

January 30, 2015, do the preventive 

modification, including HFEC inspections for 

cracking and applicable corrective actions, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1261, Revision 1, 

dated January 30, 2015, except as required by 

paragraph (i)(3) of this AD. Do all applicable 

corrective actions before further flight. 

Accomplishing the modification required by 

this paragraph terminates the inspections 

required by paragraph (g)(1) of this AD for 

the modified area only. 

(l) Terminating Action 

(1) For Groups 4 through 6, Configurations 

1, 3, 4, and 6 airplanes; and Groups 8 through 

11, Configurations 1, 3, 4, and 6 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Accomplishing the preventive 

modification, including HFEC inspections for 

cracking and applicable corrective actions, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1261, Revision 1, 

dated January 30, 2015, except as required by 

paragraph (i)(3) of this AD, terminates the 

inspections required by paragraph (g)(1) of 

this AD for the modified area only. 

(2) For Groups 4 through 6, Configurations 

3 and 6 airplanes; and Groups 8 through 11, 

Configurations 3 and 6 airplanes; as 

identified in Boeing Alert Service Bulletin 

737–53A1261, Revision 1, dated January 30, 

2015: Accomplishing the repair, including 

HFEC inspections for cracking and applicable 

corrective actions, in accordance with Part 3 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1261, 

Revision 1, dated January 30, 2015, except as 

required by paragraph (i)(3) of this AD, 

terminates the repetitive inspections required 

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

preventive modification required by 

paragraph (k) of this AD, for the repaired area 

only. 

(3) Accomplishment of the repair or the 

preventive modification specified in Boeing 

Message M–7200–02–1294, dated August 20, 

2002, before the effective date of this AD 

terminates the repetitive inspections required 

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

preventive modification required by 

paragraph (k) of this AD for the repaired or 

modified area only. 

(m) Credit for Previous Actions 

(1) This paragraph provides credit for the 

inspections required by paragraph (g) of this 

AD, if those inspections were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 737–53A1261, 

dated January 19, 2006, which was 

incorporated by reference in AD 2008–13–12, 

Amendment 39–15575 (73 FR 38905, July 8, 

2008) (‘‘AD 2008–13–12’’). 

(2) This paragraph provides credit for the 

modification specified in paragraphs (k) and 

(l)(1) of this AD, if the modification was 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 737– 

53A1261, dated January 19, 2006, which was 

incorporated by reference in AD 2008–13–12. 

(3) This paragraph provides credit for 

repairs specified in paragraphs (l)(2) of this 

AD, if those repairs were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 737–53A1261, dated 

January 19, 2006, which was incorporated by 

reference in AD 2008–13–12. 

(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 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2008–13–12 

and AD 2008–13–12 R1 are approved as 

AMOCs for the corresponding provisions of 

paragraph (g) of this AD. 

(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)(3) and (p)(4) 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. 

(i) Boeing Alert Service Bulletin 737– 

53A1261, Revision 1, dated January 30, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740; 

telephone 562–797–1717; 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/ibrlocations.html. 

Issued in Renton, Washington, on February 

1, 2017. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2017–03265 Filed 2–24–17; 8:45 am] 

BILLING CODE 4910–13–P 


sradovich on DSK3GMQ082PROD with RULES