### 73949 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations

Section 226.3—Exempt Transactions

* * * * *

3(b) Credit over applicable threshold

amount.

1. * * * vii. From January 1, 2016 through December 31, 2016, the threshold
amount is $54,600.

* * * * *

BUREAU OF CONSUMER FINANCIAL

PROTECTION

Authority and Issuance

For the reasons set forth in the preamble, the Bureau amends Regulation Z, 12 CFR part 1026, as set
forth below:

**PART 1026—TRUTH IN LENDING (REGULATION Z)** 

■ 3. The authority citation for part 1026
continues to read as follows:

Authority: 12 U.S.C. 2601, 2603–2605,

2607, 2609, 2617, 3353, 5511, 5512, 5532, 5581; 15 U.S.C. 1601 et seq.

■ 4. In Supplement I to part 1026, under Section 1026.3—Exempt Transactions,
under 3(b) Credit Over Applicable Threshold Amount, paragraph 1.vii is
added to read as follows:

Supplement I to Part 1026—Official Interpretations

* * * * *

**Subpart A—General**

* * * * *

Section 1026.3—Exempt Transactions

* * * * *

3(b) Credit Over Applicable Threshold

Amount

1. * * * vii. From January 1, 2016 through December 31, 2016, the threshold
amount is $54,600.

* * * * *

By order of the Board of Governors of the Federal Reserve System, November 18, 2015.

Robert deV. Frierson,
Secretary of the Board.

Dated: September 22, 2015.
Richard Cordray,
Director, Bureau of Consumer Financial

Protection.

[FR Doc. 2015–30091 Filed 11–25–15; 8:45 am]

**BILLING CODE: 6210–01–P; 4810–AM–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0346; Directorate Identifier 2014–NM–010–AD; Amendment**  **39–18324; AD 2015–23–08]**

**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 737–100,– 200,–200C,–300,–400, and –500 series airplanes. This AD was prompted by reports of cracks in fuselage frames, and a report of a missing strap that was not installed on a fuselage frame during production. This AD requires an inspection to determine if the strap adjacent to a certain stringer is installed, and repair if it is missing; repetitive inspections of the frame for cracking or a severed frame web; and related investigative and corrective actions if necessary. This AD also provides optional actions to terminate certain repetitive inspections. We are issuing this AD to detect and correct missing fuselage frame straps and frame cracking that can result in severed frames which, with multiple adjacent severed frames,
or the combination of a severed frame and fuselage skin chemical mill cracks,
can result in uncontrolled decompression of the airplane.

**DATES :**  This AD is effective January 4,

2016.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 4, 2016.

**ADDRESSES :**  For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA,
call 425–227–1221. It is also available
on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014–

0346.’’ 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–2014– 0346; 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, 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 by adding an AD that would apply to certain The Boeing Company Model 737–100,–200,–200C–300,–400, and–500 series airplanes. The NPRM published in the Federal Register on June 30, 2014 (79 FR 36672). The NPRM was prompted by reports of cracks in fuselage frames, and a report of a missing strap that was not installed on a fuselage frame during production. The NPRM proposed to require an inspection to determine if the strap adjacent to a certain stringer is installed, and repair if it is missing; repetitive inspections of the frame for cracking or a severed frame web; and related investigative and corrective actions if necessary. The NPRM also provided optional actions to terminate certain repetitive inspections. We are issuing this AD to detect and correct missing fuselage frame straps and frame cracking
that can result in severed frames. Continued operation of the airplane with multiple adjacent severed frames,
or the combination of a severed frame and fuselage skin chemical mill cracks,
can result in uncontrolled decompression 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 (79 FR 36672,


### 73950 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations

June 30, 2014) and the FAA’s response
to each comment.

Effect of Winglets on AD

Aviation Partners Boeing stated that installation of winglets per Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/ Regulatory

_ and

_ Guidance

_Library/ rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/ $FILE/ST01219SE.pdf ) does not affect the actions specified in the NPRM (79 FR 36672, June 30, 2014.

We concur with the commenter. We have redesignated paragraph (c) of the proposed AD (79 FR 36672, June 30, 2014) as paragraph (c)(1) of this AD, and have 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.

Request To Revise Preamble Wording

Boeing noted that the SUMMARY of the NPRM (79 FR 36672, June 30, 2014) explained that some optional actions would terminate ‘‘certain’’ repetitive inspections. Boeing requested that we use this same wording in the Proposed AD Requirements section of the NPRM (which omitted the word ‘‘certain’’).

Although we agree with the commenter’s statement, the Proposed AD Requirements section is not repeated in a final rule. Since the
referenced omission does not affect the required actions or the unsafe condition, no changes to this final rule are needed.

Request To Specify Inspection Method

Boeing requested that we add an inspection in paragraph (g) of the proposed AD (79 FR 36672, June 30, 2014). Boeing stated that this is consistent with the compliance information described in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013.

We agree with the commenter’s request. We inadvertently omitted the inspection requirement in paragraph (g) of the proposed AD (79 FR 36672, June 30, 2014), which is described in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. We have revised paragraph (g) of this AD to require that the inspection and applicable repair be done by using a method approved in accordance with the procedures specified in paragraph (q) of this AD. Paragraph (g) of this AD applies only to airplanes identified as Group 1 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. Currently, there are no Group 1 airplanes in service in the United States, so notice of this new requirement is not

necessary.
Request To Revise Terminating Action Wording

Boeing requested that we revise the wording in paragraphs (i) and (j) of the proposed AD (79 FR 36672, June 30, 2014) to state the following actions.

• Doing the repair or preventive
modification of the frame at station 328 terminates the applicable repetitive inspection requirements.

• Doing the preventive modification
of the frame at station 360 terminates the applicable station 360 inspection requirements.

• Doing the repair or preventive modification of the frame at station 328, and doing the preventive modification
of the frame at station 360 terminates the applicable repetitive inspection requirements of the frame at station 344, and the Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, skin inspections.

Boeing stated that the proposed wording in paragraphs (i) and (j) of the proposed AD (79 FR 36672, June 30, 2014) is not clear. Boeing stated that inspections of the frame at station 328 or at station 360 can be terminated by a single action (applicable repair or modification). Boeing explained that accomplishing both specified actions at
station 328 and station 360 terminates the station 344 frame inspections and the option 2 skin inspections.

We agree to clarify the acceptable terminating actions. We have added new paragraph (m) of this AD, which provides the following terminating actions. We have redesignated subsequent paragraphs accordingly.

• Accomplishing the repair or preventive modification of the frame at station 328 terminates the inspections of that frame required by paragraphs (i), (j), and (k) of this AD.

• Accomplishing the repair or preventive modification of the frame at station 328 and the preventive modification of the frame at station 360, terminates the inspections of the frame at station 344 and the fuselage skin inspections required by paragraphs (i) and (j) of this AD.

• Accomplishing the repair or preventive modification of the frame at station 360 terminates the inspections of that frame required by paragraphs (i) and (j) of this AD.

• Accomplishing the repair or preventive modification of the frame at station 328 terminates the fuselage skin inspections and the station 328 frame inspections required by paragraphs (i) and (j) of this AD.

Recommendation To Specify Optional
Preventive Modification

Boeing recommended that we specify in paragraphs (i) and (j) of the proposed AD (79 FR 36672, June 30, 2014) that the station 328 repair described in Boeing Alert Service Bulletin 737– 53A1323, dated December 6, 2013, can be used as an optional preventive
modification.

We partially agree with the commenter’s request. The commenter’s request is already addressed in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. However, additional text might help clarify this provision. We have added additional text to paragraphs (i), (j), and (k) of this AD that operators may do the repair of the frame at station 328, as specified in paragraph (m) of this AD, as an optional preventive modification for that frame.

Requests To Revise Paragraph Format and Inspection Method

Boeing requested that we revise paragraphs (i) and (j) of the proposed AD (79 FR 36672, June 30, 2014) by moving the requirements for Group 6 airplanes to a new paragraph. Boeing
stated that the service information for Group 6 airplanes provides directed inspection instructions for the station 328 frame only, as provided in table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1323, dated December 6, 2013. Boeing added that for Group 6 airplanes, there are no directed inspections for station 344 or station 360, but there are related investigative and corrective actions for detailed inspections of the
frame at station 312 and station 344.

Southwest Airlines (SWA) requested that we specify that the frame at station 344 requires detailed inspections, not detailed and eddy current inspections. SWA stated that Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, describes only detailed inspections at station 344.

We partially agree with both commenters. We disagree with making the changes requested by the commenters. However, we agree that certain actions are only done at certain locations and for certain airplanes. The inspections at station 344 are detailed inspections only. Application of the


### 73951 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations

appropriate inspection method to a given frame is addressed by the phrase ‘‘as applicable,’’ i.e., actions are applicable to the frames identified in the service information for each group of airplane. We have revised paragraphs (i)(1), (i)(2)(i), (i)(2)(ii), (j)(l), and (j)(2) of this AD by adding ‘‘as applicable’’ after
the station locations. This revision clarifies that those actions are done only as specified in the service information.

Request To Add Sub-Paragraph
Headers

Boeing requested that we add the subtitles ‘‘Initial Inspections’’ and ‘‘Follow-on Inspections’’ to paragraphs (i)(1) and (i)(2), respectively, of the proposed AD (79 FR 36672, June 30, 2014). Boeing also requested that we change the wording in paragraph (i)(2) the proposed AD to ‘‘Accomplishing the follow-on inspections required by paragraph (i)(2) of this AD,’’ instead of ‘‘Accomplishing the initial inspections . . . ’’ Boeing stated that paragraph (i) of the proposed AD would mandate the inspections for airplanes with fewer than 28,300 total flight cycles, where compliance (tables 4, 7, and 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013) consists of initial inspections and then follow-on inspections that contain options. Boeing explained that paragraph (i)(1) of the proposed AD would mandate the initial inspections, and paragraph (i)(2) of the proposed AD would mandate the follow-on inspections. Boeing also explained that paragraph (i)(2) of the proposed AD phrase ‘‘accomplishing the initial inspections’’ is understood to refer to the first follow-on inspection directed by the compliance time (threshold).

We do not agree with the commenter’s request. Paragraph (i)(2) of this AD follows the format of Boeing’s service bulletin compliance tables, which has a different repeat interval from the inspections specified in paragraph (i)(1) of this AD. Paragraphs (i)(1) and (i)(2) of
this AD contain both initial and repetitive inspections as well as related investigative actions. We have not changed this AD in this regard.

Request To Revise Repetitive Inspection Wording

Boeing requested that we revise the last sentence of paragraph (i)(2)(ii) of the proposed AD (79 FR 36672, June 30, 2014) to state, ‘‘Repeat the inspections specified in this paragraph thereafter . . . ’’ Boeing stated that this wording would then match the wording for the repetitive inspections specified in paragraph (i)(2)(i) of the proposed AD. We agree with the commenter’s request. In this case, similar wording will provide consistent paragraph wording without changing the intent of the NPRM (79 FR 36672, June 30, 2014). We have revised the wording in paragraph (i)(2)(ii) of this AD to ‘‘Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified i n... .’’

Request To Clarify a Certain Compliance Time

Europe Airpost requested that, in order to avoid any confusion, we clearly state a compliance time for paragraph (j) of the proposed AD (79 FR 36672, June 30, 2014) for airplanes that have 28,300 total flight cycles or more. The
commenter asked whether those airplanes would fall under the condition 28,300 total flight cycles but less than 32,800 total flight cycles, or 32,800 total flight cycles or more.

We agree that clarification is necessary. In this case, paragraph (j) of this AD states to use the applicable times specified in tables 4, 5, 7, and 8, of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1323, dated December 6, 2013. Individual airplanes within an operator’s fleet could fall into different categories and thus have different compliance times. Operators are to use the appropriate compliance times and repetitive intervals based upon the applicable number of total flight cycles
that have been accumulated on each airplane as of the effective date of this AD. We have added new paragraph (n)(3) of the AD to inform operators that
the ‘‘Condition’’ columns of the compliance tables also contain compliance information that corresponds to the effective date of the AD. We have also revised paragraphs (i)(1) and (j)(1) of this AD to refer to paragraph (n)(3) of this AD.

Request To Clarify Terminating Action Wording

SWA requested that we revise the terminating action portion of paragraph (j) of the proposed AD (79 FR 36672, June 30, 2014) to clarify the specified actions. SWA stated that, as written, the terminating action statement seems to imply that the operator is required to accomplish both the preventive
modification of the frame at station 360 and the repair of the frame at station 328 to terminate the repetitive inspection requirements for any of the station 328, 344, and 360 frames. SWA also stated that the terminating action in paragraph (j) of the proposed AD does not specify actions or terminating actions if a repair
is installed at the station 344 frame. SWA explained that Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, contains terminating
action in the footnotes of the compliance tables in paragraph 1.E., ‘‘Compliance,’’ which the commenter
thinks should be restated in the AD.

We agree with the commenter’s request. For clarity, we have moved the terminating action provisions that were specified in paragraphs (i)(1), (i)(2), (j), and (k) of the proposed AD (79 FR 36672, June 30, 2014) to new paragraphs (m)(1) through (m)(4) of this AD. We have redesignated subsequent paragraphs accordingly.

Requests To Specify Eddy Current Inspection

Europe Airpost requested that we clarify whether we meant to exclude the eddy current inspection at station 328 described in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, in paragraph (k) of the proposed AD (79 FR 36672, June 30, 2014). Boeing requested that we add the eddy current inspection at station 328 described in Boeing Alert Service Bulletin 737– 53A1323, dated December 6, 2013, in paragraph (k) of the proposed AD.

We agree with Boeing’s request to specify the eddy current inspection and Europe Airpost’s request to clarify the eddy current inspection requirement. We inadvertently omitted the eddy current inspection from paragraph (k) of the proposed AD (79 FR 36672, June 30, 2014) which applies to Group 7 airplanes. Our intention was to match the actions described in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. In the NPRM (79 FR 36672, June 30, 2014), we did not identify any differences with Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, in regards to the required inspections, which includes repetitive eddy current inspections at station 328. For Groups 2 through 7 airplanes, paragraphs (i) and (j) of the proposed AD do specify detailed and HFEC inspections for Groups 2 through 6 airplanes. Therefore, we have revised paragraph (k) of this AD to specify doing eddy current inspections, in addition to the detailed inspections, of the frame at station 328 for Group 7 airplanes.

Request To Specify Terminating
Actions for Station 380

SWA requested that we specify procedures or terminating actions for repairs installed at the station 380 frame, since paragraph (l) of the proposed AD (79 FR 36672, June 30, 2014) does not specify such actions.


### 73952 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations

We do not agree with the commenter’s request. Boeing has not provided such repairs for our approval in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. Therefore, we have no specific engineering data to review and approve. We have not changed this AD in this regard.

Request for Credit for Certain Repairs

SWA requested that we revise paragraphs (i) through (l) of the proposed AD (79 FR 36672, June 30, 2014) to include provisions for existing repairs that were done using the service repair manual (SRM) or the original equipment manufacturer (OEM) instructions. SWA requested that the
NPRM be revised to either terminate the inspections or include alternative actions if existing repairs inhibit the ability to perform the inspections.

We partially agree with the commenter’s request. We agree that repairs approved by Boeing via FAA Form 8100–9 (Statement of Compliance with Airworthiness Standards) would have also included the appropriate inspections. We disagree that SRM repairs would necessarily provide the same level of safety. The commenter did not specify for which SRM repairs it was requesting approval. Such repairs might or might not have included consideration of the safety issues addressed by Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, and this AD ( e.g., skin cracking combined with frame cracking). We have added a new paragraph (p) to this AD to provide credit for repairs of the station 328, 344, 360, and 380 frames in the areas addressed by this AD that have been approved by the Boeing ODA via FAA Form 8100–9 prior to the effective date of this AD for the repairs specified in paragraphs (i), (j), (k), and (l) of this AD. We have redesignated subsequent paragraphs accordingly.

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 (79 FR 36672, June 30, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 36672, June 30, 2014).

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 737–53A1323, dated December 6, 2013. The service information describes procedures for inspection for cracking and missing straps, modification, and repair of certain fuselage frames. 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 of this AD.

Costs of Compliance

We estimate that this AD affects 417 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### C OSTS

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

Inspections .................... 21 work-hours × $85 per hour = $1,785 per inspection cycle. $0 $1,785 per inspection cycle. $744,345 per inspection cycle.

We have received no definitive data that would enable us to provide cost
estimates for certain on-condition actions specified in this AD. However, we estimate the following costs to do any necessary repairs of the station 328 frame and the station 360 frame. We have no way of determining the number of aircraft that might need these repairs:



### O N 

### -C ONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Frame 328 repair ............................... 25 work-hours × $85 per hour = $2,125 ...................................................... Negligible ... $2,125 Frame 360 repair ............................... 5 work-hours × $85 per hour = $425 ........................................................... Negligible ... 425

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.


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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):

2015–23–08 The Boeing Company: Amendment 39–18324; Docket No. FAA–2014–0436; Directorate Identifier

2014–NM–010–AD.

(a) Effective Date

This AD is effective January 4, 2016.

(b) Affected ADs

None.

(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 737–53A1323, dated December 6, 2013.

(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 ST01920SE 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 cracks in fuselage frames, and a report of a missing strap that was not installed on a fuselage frame during production. We are issuing this AD to detect and correct missing fuselage frame straps and frame cracking that can result in severed frames. Continued operation of the airplane with multiple adjacent severed frames, or the combination of a severed frame and fuselage skin chemical mill cracks, can result in uncontrolled decompression of the airplane. (f) Compliance
Comply with this AD within the compliance times specified, unless already
done.

(g) Actions for Group 1 Airplanes

For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (n)(1) of this AD, do the inspection for cracking of the frames and applicable repairs using a method approved in accordance with the procedures specified in paragraph (q) of this

AD.

(h) Groups 2 Through 7 Airplanes: Inspection for Strap Installation at Station

312

For airplanes identified as Groups 2 through 7 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in tables 2 and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (n)(1) of this AD, do a general visual inspection of the frame at station 312 to determine if the strap adjacent to stringer S–22 right is installed, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. If the strap is not installed, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (q) of this

AD.

(i) Groups 2 Through 6 Airplanes With Less Than 28,300 Total Flight Cycles: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Stations 328, 344,
and 360

For airplanes identified as Groups 2 through 6 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, that have accumulated less than 28,300 total flight cycles as of the effective date of this AD: Do the actions required by paragraphs (i)(1) and (i)(2) of this AD. Operators may do the repair of the frame at station 328 as specified in paragraph (m) of this AD as an optional preventive modification for that
frame.

(1) At the applicable times specified in tables 4, 5, 7, and 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraphs (n)(1) and (n)(3) of this AD: Do detailed and eddy current inspections of the frame at stations 328, 344, and 360, as applicable, for cracking or a severed frame web; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (n)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, until the inspection required by paragraph (i)(2) of this AD is
done.

(2) At the applicable time specified in tables 4, 5, 7, and 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, do the actions specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. Accomplishing the initial inspections required by paragraph (i)(2) of this AD terminates the inspections required by paragraph (i)(1) of this AD.

(i) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360, as applicable, for cracking or a severed frame web; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (n)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6,

2013.

(ii) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360, as applicable, for cracking or a severed frame web; and external detailed and eddy current inspections of the fuselage skin for cracking; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (n)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6,

2013.

(j) Groups 2 Through 6 Airplanes With 28,300 Total Flight Cycles or More: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Stations 328, 344, and 360

For airplanes identified as Groups 2 through 6 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, that have accumulated 28,300 total flight cycles
or more as of the effective date of this AD: At the applicable times specified in tables 4, 5, 7, and 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1323, dated December 6, 2013, except as provided by paragraphs (n)(1) and (n)(3) of this AD, do the inspections specified in paragraph (j)(1) or (j)(2) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (n)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections specified in paragraph (j)(1) or


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(j)(2) of this AD thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. Operators may do the repair of the frame at station 328, as specified in paragraph (m) of this AD, as an optional preventive modification for that frame.

(1) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360, as applicable, for cracking or a
severed frame web.

(2) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360, as applicable, for cracking or a severed frame web; and external detailed and eddy current inspections of the fuselage skin for cracking.

(k) Group 7 Airplanes: Repetitive Inspections, Related Investigative Actions,
and Corrective Actions at Station 328

For airplanes identified as Group 7 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in table 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (n)(1) of this AD, do a detailed inspection and eddy current inspection of the frame at station 328 for cracking or a severed frame web; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (n)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. Operators may do the repair of the frame at station 328, as specified in paragraph (m) of this AD, as an optional preventive modification for that frame.

(l) Groups 2 Through 5 Airplanes: Repetitive Inspections, Related Investigative Actions,
and Corrective Actions at Station 380

For airplanes identified as Groups 2 through 5 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in tables 9 and 10 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (n)(1) of this AD, do detailed and eddy current inspections of the frame at station 380 for cracking or a severed frame web; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (n)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. (m) Terminating Actions for Airplanes Identified as Groups 2, 3, 4, 5, 6, and 7

(1) For airplanes identified as Groups 2, 3, 4, 5, and 7 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: Accomplishing the repair or preventive modification of the frame at station 328, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as required by paragraph (n)(2) of this AD, terminates the inspections of that frame required by paragraphs (i), (j), and (k) of this

AD.

(2) For airplanes identified as Groups 2, 3, 4, and 5 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: Accomplishing the repair or preventive
modification of the frame at station 328 and the preventive modification of the frame at station 360, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as required by paragraph (n)(2) of this AD, terminates the inspections of the frame at station 344 and the fuselage skin inspections required by paragraphs (i) and (j) of this AD.

(3) For airplanes identified as Groups 2, 3, 4, and 5 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: Accomplishing the repair or preventive modification of the frame at station 360, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as required by paragraph (n)(2) of this AD, terminates the inspections of that frame required by paragraphs (i) and (j) of this AD.

(4) For airplanes identified as Group 6 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: Accomplishing the repair or preventive modification of the frame at station 328, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as required by paragraph (n)(2) of this AD, terminates the fuselage skin inspections and the station 328 frame inspections required by paragraphs (i) and (j) of this AD.

(n) Exceptions to Service Information

(1) Where Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, 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) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (q) of this AD.

(3) The Condition column of Tables 4, 5, 7, and 8 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, refers to total flight cycles ‘‘at the original issue date of this service bulletin.’’ This AD, however, applies to the airplanes with the specified total flight cycles as of the effective date of this AD. (o) Post-Repair Inspections and PostModification Inspections

(1) The post-repair and post-modification inspections specified in tables 13 through 15 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, are not required by this

AD.

(2) The post-repair and post-modification inspections specified in Tables 13 through 15 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, are not required by this AD.

(p) Credit for Previous Actions

This paragraph provides credit for repairs of the station 328, 344, 360, and 380 frames in the areas addressed by this AD that have been approved by the Boeing Organization Designation Authorization (ODA) via FAA Form 8100–9 (Statement of Compliance with Airworthiness Standards) prior to the effective date of this AD for the repairs specified in paragraphs (i), (j), (k), and (l) of
this AD.

(q) 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 (r) 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 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.

(r) Related Information

For more information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712– 4137; phone: 562–627–5324; fax: 562–627– 5210; email: galib.abumeri@faa.gov.

(s) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference


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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 this AD specifies otherwise.

(i) Boeing Alert Service Bulletin 737– 53A1323, dated December 6, 2013.

(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 October

30, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–28824 Filed 11–25–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–3642; Directorate Identifier 2015–CE–028–AD; Amendment**  **39–18335; AD 2015–24–03]**

**RIN 2120–AA64**

**Airworthiness Directives; SOCATA Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for SOCATA Model TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct
an unsafe condition on an aviation product. The MCAI describes the unsafe
condition as corrosion of the horizontal stabilizer. We are issuing this AD to require actions to address the unsafe condition on these products.

**DATES :**  This AD is effective January 4,

2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 4, 2016.

**ADDRESSES :**  You may examine the AD
docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3642; or in person at Document 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 service information identified in this AD, contact SOCATA NORTH AMERICA, North Perry Airport, 601 NE 10 Street, Pompano Beach, Florida 33060; phone: (954) 366–3331; Internet: http://www.socatanorthamerica.com/ default.htm. You may view this
referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–
4148. It is also available on the Internet

at http://www.regulations.gov by searching for Docket No. FAA–2015–

3642.

**FOR FURTHER INFORMATION CONTACT :**  Albert J. Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090; email: albert.mercado@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 SOCATA Models TB 9, TB 10, TB 20, TB 21, and TB 200 airplanes. The NPRM was published in the Federal Register on August 28, 2015 (80 FR 52215). The NPRM proposed to correct an unsafe condition for the specified products and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. The MCAI

states:

During accomplishment of SOCATA Service Bulletin (SB) SB10–152–55 at original issue, some operators reported finding heavy corrosion of the horizontal stabilizer (HS) spar.

The results of the technical investigation
have identified that the corrosion was caused by humidity ingress in the HS on aeroplanes subject to severe environmental conditions.

This condition, if not detected and corrected, could result in buckling and permanent HS distortion, possibly resulting in reduced control of the aeroplane.

To address this unsafe condition, SOCATA issued SB 10–152–55 Revision 1 to provide instructions for inspection and corrective

action.

For the reasons described above, this AD requires repetitive inspections of the affected area of the HS and, depending on findings, accomplishment of applicable corrective action(s).

The MCAI can be found in the AD
docket on the Internet at: http:// www.regulations.gov/ #!documentDetail;D=FAA-2015-3642-

0001.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and the FAA’s response to the comment.

Request

Anthony Pynes commented that that he does not believe the methodology
used and the foundational data available supports the need for this AD, and thus
he believes that this AD is not

necessary.

We do not agree. The FAA, in working with the State of Design airworthiness authority (EASA),
determined that the actions of this AD
on the horizontal stabilizer of the affected airplanes are necessary to
correct an unsafe condition. Included in this is the risk in establishing such actions at the required compliance times. No changes to the AD have been
made based on this comment.

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the 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 NPRM (80 FR 52215, August 28, 2015) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 52215, August 28, 2015).

Related Service Information Under 1

CFR Part 51

We reviewed DAHER–SOCATA TB Aircraft Mandatory Service Bulletin SB 10–152, Amendment 1, dated April
2015. The service information describes procedures for inspection for corrosion on the horizontal stabilizer spar and repair, if necessary. 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 of the AD.