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(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– 53A2808, dated November 30, 2012.

(ii) Boeing Service Bulletin 747–53A2465, Revision 5, dated July 11, 2013.

(iii) Boeing Service Bulletin 747–53A2562, Revision 3, dated July 11, 2013.

(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 the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this service information that is incorporated by reference at the
National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Renton, Washington, on March 9,

2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–06001 Filed 3–17–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0495; Directorate Identifier 2014–NM–172–AD; Amendment**  **39–18435; AD 2016–06–04]**

**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 cracking
at certain fastener locations in the
window corners of the window belt area. This AD requires repetitive high frequency eddy current (HFEC) inspections for fatigue cracking in
certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions if necessary. This AD also provides an optional preventive
modification that terminates the inspections at the modified location. We are issuing this AD to detect and correct fatigue cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane.

**DATES :**  This AD is effective April 22,

2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 22, 2016.

**ADDRESSES :**  For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also
available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–

0495.

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– 0495; 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 :**  Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5264; fax: 562–627– 5210; email: jennifer.tsakoumakis@ 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 March 24, 2015 (80 FR 15523) (‘‘the NPRM’’). The NPRM was prompted by reports of cracking at
certain fastener locations in the window
corners of the window belt area. The NPRM proposed to require repetitive HFEC inspections for fatigue cracking in
certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of 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.

Request for Clarification of Location of the Twelve Fastener Inspections

Southwest Airlines (SWA) requested that a correction be made to paragraph (g) of the proposed AD to clarify the areas for the inspection of the twelve
fastener locations. SWA noted that paragraph (g) of the proposed AD stated to inspect locations ‘‘at the upper
forward and lower aft corners of each window between station (STA) 360 and
STA 540 and between STA 727 and
STA 908.’’ SWA stated that between STA 727 and STA 908, Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, specifies the location as the lower forward and upper aft corners.

We agree with the commenter for the reason provided. We have revised paragraph (g) of this AD to require an inspection of the twelve fastener locations at the upper forward and
lower aft corners of each window
between STA 360 and STA 540 and at the upper aft and lower forward corners
of each window between STA 727 and

STA 908.

Request for Clarification of the Intent of the Inspection Requirements in Paragraph (g) of the Proposed AD

SWA requested that we clarify the intent of paragraph (g) of the proposed AD. SWA stated that paragraph (g) of the proposed AD states to accomplish the inspections at the times specified in tables 1 and 2 of paragraph 1.E.,


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‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, and then repeat the inspections at the applicable times specified in tables 1 and 2 until ‘‘the terminating action in paragraph (h) of this AD is accomplished,’’ which is the optional preventive modification in Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014. SWA stated that, per note (b) in tables 1 and 2, accomplishment of the preventive modification in accordance with Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, is terminating action for both the initial and repeat inspections at the modified locations. SWA stated that paragraph (g) of the proposed AD does not mention the option to accomplish the actions specified in paragraph (h) of the proposed AD in lieu of the initial inspection specified in paragraph (g) of this AD; it only states to ‘‘repeat the inspections . . . until the terminating action specified in paragraph (h) of this
AD is done.’’ SWA noted it is unclear if the intent of paragraph (g) of this AD is to require accomplishment of the Part 1 external surface HFEC inspections of the skin prior to accomplishing the Part 3 preventive modification instructions, or if the intent of paragraph (g) of the proposed AD is to provide the operator the option to accomplish paragraph (h) of the proposed AD (preventive modification) in lieu of accomplishing paragraph (g) of the proposed AD (inspections), since the Part 3 modification instructions include open hole HFEC inspections of the skin.

We agree to provide clarification. Paragraph (g) of this AD is not required at the time of accomplishment of the preventive modification specified in paragraph (h) of this AD. Paragraph (h) of this AD states that the preventive modification (including all applicable related investigative and corrective actions) terminates the inspections in paragraph (g) of this AD. This means all inspections (initial and repetitive) in paragraph (g) of this AD are not required if paragraph (h) of this AD is done. We have not changed this AD in this regard.

Request for Clarification of Existing Repairs

SWA requested clarification about existing repairs that meet the requirements of note (a) in tables 1 and 2 of paragraph l.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1328, dated July 22, 2014. SWA also requested to extend the note to apply to existing repairs that address damage other than cracking, provided that the repairs are evaluated and approved by Boeing via an FAA Form 8100–9. In addition, SWA requested we clarify whether note (a) applies only to reinforcing repairs that encompass all
twelve fastener locations at a window corner, or if note (a) also applies to existing non-reinforcing oversize hole repairs.

We partially agree with the commenter. We agree with adding a paragraph to this AD to provide credit for previously approved repairs to address cracking issues, because Boeing Organization Designation Authorization (ODA) approved repairs installed prior
the effective date of this AD are acceptable for terminating the initial and repetitive inspections in the area under the repair. We disagree with allowing any other repair as an alternative method of compliance (AMOC) because other repairs may or may not address the cracking issue. However, operators may request approval of an AMOC for these repairs using the procedures specified in paragraph (l) of this AD.

We have added new paragraph (g)(1) to this AD to specify that the inspections required by the introductory text of paragraph (g) of this AD may be terminated in areas with repairs installed prior to the effective date of this AD, provided the repairs are reinforcing and address the cracking issue addressed in this AD, and installation was approved by the Boeing Commercial Airplanes ODA via FAA

Form 8100–9.

Request for Clarification of the Termination of Inspection for Repaired Area for Group 1 Airplanes

All Nippon Airways (ANA) requested we clarify if, for Group 1 airplanes as identified in paragraph 1.A.1 ‘‘Effectivity,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, areas repaired using Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, is terminating action for the repaired area. ANA pointed out that table 1 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, includes this wording.

We agree to provide clarification. Accomplishing a repair in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, also terminates the inspection of the repaired area for Group 1 airplanes. We have added new paragraph (g)(2) to this AD to specify that repairs done in
accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, terminate the inspection required by paragraph (g) of this AD in only the repaired area for Group 1 airplanes only.

Request To Include Provisions for Airplanes Previously Inspected, Modified, and/or Repaired

SWA requested that we revise the NPRM to include provisions for airplanes that were previously inspected, modified, and/or repaired using step 3 of the Accomplishment Instructions of Boeing Service Bulletin 737–53–1306, dated September 22, 2010; Revision 1, dated March 17, 2010; Revision 2, dated October 25, 2011; or Revision 3, dated January 22, 2014; as terminating action for the inspections required by paragraph (g) of the proposed AD, as well as any
documented deviations that were approved by the Boeing ODA via an

FAA Form 8100–9.

SWA stated that step 3 of Boeing Service Bulletin 737–53–1306 (all revisions) includes inspection, preventive modification, and repair
instructions for the window corner locations addressed by the proposed AD. Figures 8 through 10 of Boeing Service Bulletin 737–53–1306 (all revisions) provide inspection and preventive modification instructions,
which also include instructions for a fastener oversize repair, edge margin requirements, and window forging replacement. Figures 13 through 18 provide external reinforcing repair instructions. Figures 40 through 43 were added in Boeing Service Bulletin 737– 53–1306, Revision 3, dated January 22, 2014, to incorporate the option to replace the window belt panels in lieu of accomplishing the window corner inspections, preventive modification, and approved repairs. SWA stated that it considers the instructions in Step 3 of Boeing Service Bulletin 737–53–1306 (all revisions) to meet the intent of the proposed AD since the instructions
address and eliminate the unsafe condition that prompted the proposed

AD.

We do not agree to revise this AD because Boeing Service Bulletin 737– 53–1306 is specific for SWA. We do not consider it appropriate to include various provisions in an AD applicable only to a single operator’s unique configuration of affected airplanes. However, SWA may submit a request for an approval of an AMOC using the procedures specified in paragraph (l) of this AD. We have not changed this AD in this regard.

Requests To Clarify Required Actions

SWA and ANA requested that we clarify which actions specified in Boeing Alert Service Bulletin 737–


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53A1328, dated July 22, 2014, are required. SWA stated that paragraph (j)(3) of the proposed AD (paragraph (l)(3) in this AD) indicates that steps identified as ‘‘RC’’ (Required for Compliance) in Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, must be accomplished ‘‘in order to comply with this AD.’’

The commenters noted that there are ‘‘RC’’ steps in Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, that are not clearly addressed in the proposed AD. SWA noted that Parts 7 and 8 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, contain steps that are identified as ‘‘RC;’’ however, the proposed AD does not mention the compliance times for
these actions. SWA stated that Part 7 of Boeing Alert Service Bulletin 737– 53A1328, dated July 22, 2014, provides window frame replacement instructions, and steps 5 and 6 in Part 8 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, provide post-repair/ post-modification inspection
instructions for window frames with short edge margin conditions at the compliance times specified in tables 3, 4, and 8 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014. SWA
assumed that actions identified in Table 3 and Table 8 are not required for compliance and that the actions identified in Table 4 are required for compliance. SWA also pointed out that step 10 of Part 2 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, is not ‘‘RC,’’ but could result in accomplishment of Part 7 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, which has ‘‘RC’’ steps.

We agree to clarify the actionsrequired by this AD. The postmodification and post-repair inspections identified in Table 4 and Table 5 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, are required by this AD. The accomplishment instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, are unclear. Therefore, we have added new paragraph (i) to this AD to specify the
actions identified in Table 4 and Table 5 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1328, dated July 22, 2014. We have redesignated subsequent paragraphs accordingly.

Regarding Part 7 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, if operators chose to do the modification, certain actions specified in Part 3, Part 4, and Part 5 of Boeing Alert Service Bulletin 737– 53A1328, dated July 22, 2014, are identified as ‘‘RC’’ steps. Within those steps, there is an on-condition action, which specifies to do Part 7; thus, step 1 of Part 7 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014 is required for compliance.

Steps 2, 3, and 4 of Part 8 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, are referenced in Table 3 and Table 8 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, and are not required by this AD. We have added new paragraph (k) ofthis AD to clarify that the postmodification inspections specified in Table 3 and Table 8 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, are airworthiness limitations that are required by maintenance and operational rules; therefore, these inspections are not required by this AD. We have redesignated subsequent paragraphs accordingly.

Request To Clarify Office Responsible
for AMOCs

ANA requested that we clarify the office responsible for AMOCs. ANA stated that paragraph (j) of the proposed AD specifies that the Seattle ACO has the authority to approve AMOCs. However, ANA noted it has seen other ADs for out of production airplanes that refer to the Los Angeles ACO.

We agree to clarify. The Los Angeles ACO is currently responsible for AMOCs for the airplanes identified in this AD. We have revised paragraphs (l)(1) and (l)(4) of this AD (paragraphs (j)(1) and (j)(4) of the proposed AD) to refer to the Los Angeles ACO.

Requests for Clarification of Incorrect
References

Boeing and SWA requested that we clarify incorrect references in Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014. The commenters stated that note (e) in Figure 5 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, incorrectly references table 2 of paragraph 3.B., Work Instructions, for post repair/ modification inspections of short edge margins on window frames. The
commenters stated that these references should be to table 3 of paragraph 3.B., Work Instructions. Boeing also identified the notes in figures 9, 10, 11,
and 12 as additional locations where the
reference to table 2 should be to table 3. The commenters requested that we clarify in this AD that repeat post repair and modification inspections for window frames with short edge margins
are defined in table 3 rather than table 2 of paragraph 3.B, Work Instructions, in Boeing Alert Service Bulletin 737– 53A1328, dated July 22, 2014.

We agree with the commenters that the identified table references in Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, are incorrect. We have added new paragraphs (j)(3) and (j)(4) to this AD to specify the correct
table references. We have also added new paragraph (j)(5) to this AD to clarify that operators must comply with the edge margin requirements in Table 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737– 53A1328, dated July 22, 2014. We have also revised paragraphs (g) and (h) of
this AD to include references to paragraphs (j)(3), (j)(4), and (j)(5) of this

AD.

Effect of Winglets on 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/ be866b732f6cf31086257b9700692796/ $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) of this AD and 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 AD. 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.

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 737–53A1328, dated July 22,
2014. The service information describes procedures for HFEC inspections for


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fatigue cracking in certain fastener

locations in the window corners of the window belt area, 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 142 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS 

### : R EQUIRED 

### A CTIONS

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

Inspection ......... Up to 2,312 work-hours × $85 per hour = $196,520 per inspection cycle. $0 Up to $196,520 per inspection cycle. Up to $27,905,840 per inspection cycle.



### E STIMATED 

### C OSTS 

### : R EQUIRED 

### A CTIONS

Action Labor cost Parts cost Cost per product

Preventive modification ................................................ 108 work-hours × $85 per hour = $9,180 .................... $0 $9,180

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 repairs:



### O N 

### -C ONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Repair ............... Up to 18 work-hours × $85 per hour = $1,530 per repair .................................. $0 Up to $1,530 per repair.

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): 2016–06–04 The Boeing Company: Amendment 39–18435 ; Docket No. FAA–2015–0495; Directorate Identifier

2014–NM–172–AD.

(a) Effective Date

This AD is effective April 22, 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 737–53A1328, dated July 22, 2014.

(2) Installation of Supplemental Type Certificate (STC) ST01219SE (http:// rgl.faa.gov/Regulatory

_ and

_ Guidance

_ Library/rgstc.nsf/0/ be866b732f6cf31086257b9700692796/$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 at certain fastener locations
in the window corners of the window belt area. We are issuing this AD to detect and correct fatigue cracking around the fastener


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locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified, unless already
done.

(g) Inspections

At the applicable time specified in tables 1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, except as required by paragraph (j)(1) of this AD: Do external surface high frequency eddy current (HFEC) inspections for cracking of the skin at the 12 fastener locations at the upper forward and
lower aft corners of each window between station (STA) 360 and STA 540 and at the upper aft and lower forward corners of eachwindow between STA 727 and STA 908, leftside and right-side of the fuselage, at and between stringers S–11 and S–13; and all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, except as required by paragraphs (j)(2), (j)(3), (j)(4), and (j)(5) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in tables 1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014. Accomplishing the preventive modification specified in paragraph (h) of this AD terminates the repetitive inspections required by this paragraph at the modified location only.

(1) The inspections required by the introductory text of paragraph (g) of this AD may be terminated in areas with repairs installed prior to the effective date of this AD, provided the repairs are reinforcing and address the cracking issue identified in this AD, and installation was approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) via FAA

Form 8100–9.

(2) For Group 1 airplanes identified in Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014: Window corner crack repairs terminate the inspection required by the introductory text of paragraph (g) of this AD in the repaired area only. The repair, including all applicable related investigative and corrective actions, must be done in
accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, except as required by paragraphs (j)(2), (j)(3), (j)(4), and (j)(5) of this AD.

(h) Preventive Modification

Accomplishment of a preventive
modification in the fastener locations in the
window corners of the window belt area
between STA 360 and STA 540 and betweenSTA 727 and STA 908, left-side and rightside of the fuselage, at and between stringers S–11 and S–13, terminates the inspections required by paragraph (g) of this AD at the modified location only. The modification, including all applicable related investigative and corrective actions, must be done in
accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, except as required by paragraphs (j)(2), (j)(3), (j)(4), and (j)(5) of this AD.

(i) Repetitive Inspections, Replacements, and

Corrective Actions

For airplanes having any condition identified in Table 4 or Table 5 of paragraph l.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014: At the applicable times specified in Table 4 and Table 5 of paragraph l.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1328, dated July 22, 2014, do a window frame replacement or an internal detailed inspection for cracks of the window forging around the fastener collars, as applicable, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, except as required by paragraphs (j)(2), (j)(3), (j)(4), and (j)(5) of this AD. Repeat the inspections at the applicable times specified in table 4 and table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014.

(j) Exceptions to the Service Information Specifications

(1) Where Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, specifies a compliance time ‘‘after the original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of
this AD.

(2) Where Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Although Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, specifies to contact Boeing for repair instructions, and specifies that action as Required for Compliance (RC), this AD requires repair as specified in this paragraph.

(3) Where note (e) of Figure 5 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, specifies to ‘‘Refer to Paragraph 3.B., Work Instructions, Table 2 for edge margin requirements,’’ operators must comply with Table 3 of paragraph 3.B., ‘‘Work Instructions,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, for edge margin requirements.

(4) Where the notes for fastener codes A and B in figures 9, 10, 11, and 12 of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, refer to ‘‘Paragraph 3.B., Work Instructions, Table 2’’ for edge margin requirements, operators must comply with Table 3 of paragraph 3.B., ‘‘Work Instructions,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, for edge margin requirements.

(5) Where note (e) of figures 6, 7, and 8 and step 1.a.(1) of Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, specifies to ‘‘Refer to Paragraph 3.B., Work Instructions, Table 3 for edge margin requirements,’’ operators must comply with Table 3 of paragraph 3.B., ‘‘Work Instructions,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 2014, for edge margin requirements.

(k) Post-Repair Inspections/PostModification Inspections

Table 3 and Table 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1328, dated July 22, 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) Except as required by paragraph (j)(2)

of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (l)(3)(i) and (l)(3)(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 this 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.

(4) 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 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.


### 14716 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations

(m) Related Information

For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., Lakewood, CA 90712–4137; phone: 562–627– 5264; fax: 562–627–5210; email: jennifer.tsakoumakis@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– 53A1328, dated July 22, 2014.

(ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680;

Internet https://www.myboeingfleet.com.

(4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this service information that is incorporated by reference at the
National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Renton, Washington, on March 7,

2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–05842 Filed 3–17–16; 8:45 am]

**BILLING CODE 4910–13–P**

**OFFICE OF THE UNITED STATES**
**TRADE REPRESENTATIVE**

**15 CFR Part 2017**

**[Docket Number USTR–2016–0002]**

**RIN 0350–AA07**

**Establishment of a Petition Process To Review the Eligibility of Countries** 
**Under the African Growth and Opportunity Act (AGOA)** 

**AGENCY :**  Office of the United States Trade Representative.

**ACTION :**  Interim final rule with request
for comments.

**SUMMARY :**  The Trade Preferences Extension Act of 2015 (TPEA) requires the President to establish a petition process to review the eligibility of countries for the benefits of the African Growth and Opportunity Act (AGOA). This authority has been delegated to the
Office of the United States Trade Representative (USTR).

**DATES :**  The interim final rule is effective on March 18, 2016. USTR will accept
comments on the interim final rule in writing on or before April 18, 2016.

**ADDRESSES :**  All comments must be submitted electronically at www.regulations.gov, docket number

USTR–2016–0002.

**FOR FURTHER INFORMATION CONTACT :**  For procedural questions, please contact Yvonne Jamison, Trade Policy Staff Committee, at 202–395–3475. Direct all other questions to Constance Hamilton, Deputy Assistant U.S. Trade Representative for African Affairs, at

Constance

_Hamilton@ustr.eop.gov or
202–395–9514.

**SUPPLEMENTARY INFORMATION :** 
I. Background

The AGOA (Title I of the Trade and Development Act of 2000, Pub. L. 106– 200) (19 U.S.C. 2466a et seq. ), as amended, contains provisions forenhanced trade benefits for eligible subSaharan African countries.

Section 506(c) of the TPEA, which was signed into law on June 29, 2015 (Pub. L. 114–27, sec. 105(d)(3), 129 Stat. 366–367)), requires the President to establish a process to allow any interested person, at any time, to file a petition with USTR concerning the compliance of any sub-Saharan African country listed in section 107 of the AGOA (19 U.S.C. 3706), with the eligibility requirements set forth in section 104 of the AGOA (19 U.S.C. 3703) and the eligibility criteria set forth
in section 502 of the Trade Act of 1974 (19 U.S.C. 2462). On February 26, 2016, the President delegated this authority to

USTR. See E.O. 13720 of Feb. 26, 2016,
81 FR 11087, Mar. 2, 2016.

II. Analysis of the Interim Final Rule

The interim final rule adds 15 CFR part 2017. The new Part 2017 establishes a petition process that supplements the annual (normal cycle) request for public comments on whether a beneficiary sub-Saharan African country is meeting the eligibility criteria and requirements of the AGOA program ( see, e.g., 80 FR 48951, Aug. 14, 2015).

Section 2017.0 defines acronyms used throughout Part 2017.

Section 2017.1 permits any interested party to submit a petition, at any time,regarding whether a beneficiary subSaharan African country meets the eligibility requirements in section 104 of the AGOA and the eligibility criteria in section 502 of the Trade Act of 1974. It requires that a petition adequately identify the country and the concern. A petition indicating the existence of exceptional circumstances warranting an out-of-cycle review must contain a statement of reasons explaining why an out-of-cycle review is warranted.

Section 2017.2 explains how USTR will process petitions. USTR will consider petitions filed in accordance with the public comment period of the annual (normal cycle) review of all beneficiary countries in conjunction
with that review. USTR will consider petitions filed outside of that time frame in the next (normal cycle) annual review. If USTR receives a petition outside of the annual (normal cycle) review process that indicates the existence of exceptional circumstances, the AGOA Implementation
Subcommittee will consider whether
there is a basis for the initiation of an out-of-cycle review and make recommendations to the Trade Policy Staff Committee, which will, in turn, advise the U.S. Trade Representative. If the U.S. Trade Representative finds that there are exceptional circumstances warranting an out-of-cycle review, within 30 days of that determination
USTR will announce a schedule for the
review in the Federal Register

.

Section 2017.3 requires USTR to publish a summary of the actions taken in response to petitions in the Federal Register . The notice also will include a list of pending petitions upon which no
decision has been made.

Section 2017.4 provides that all
submitted materials will be made available for public inspection at www.regulations.gov other than appropriately designated confidential
business information.

The TPEA extended the AGOA until September 30, 2025. See Pub. L. 114–27, sec. 103, 129 Stat. 364, June 29, 2015. Section 2017.5 provides that the AGOA petition process will expire on that date unless extended by statute.

III. Requirements for Submission

All submissions must be in English and must be submitted electronically

via http://www.regulations.gov. USTR will not accept hand-delivered
submissions. To make a submission using http://www.regulations.gov, enter the docket number USTR–2016–0002 in the ‘‘Search for’’ field on the home page
and click ‘‘Search.’’ The site will provide a search-results page listing all
documents associated with this docket. Find a reference to this notice by selecting ‘‘Notice’’ under ‘‘Document Type’’ in the ‘‘Filter Results by’’ section
on the left side of the screen and click