### 51447 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations

Programs, 7121 Southwest Boulevard, Wichita, KS 67215. Provide the brushes and the information specified in paragraphs (m)(1) through (m)(6) of this AD within 30 days after the replacement if the replacement was done on or after the effective date of this AD, or within 30 days after the effective date of this AD if the replacement was done before the effective date of this AD.

(1) The model and serial number of the airplane.

(2) The part number of the motor. (3) The part number of the brushes, if known.

(4) The elapsed time, in motor hours, since the last brush/motor replacement, if known.

(5) If motor hours are unknown, report the elapsed airplane flight hours since the last brush/motor replacement, and indicate that motor hours are unknown.

(6) The number of motor hours currently displayed on the pallet hour meter, if installed.

(n) Parts Installation Limitation

As of the effective date of this AD, no person may install an A/C compressor motor having P/N FWA1134104–1 or P/N FWA1134104–5, unless the inspection specified in paragraph (h) of this AD is done before installation, and the replacements specified in paragraph (i) of this AD are subsequently done in accordance with the applicable service information identified in paragraphs (j)(1) through (j)(6) of this AD at the times specified in paragraph (i) of this
AD.
(o) Special Flight Permit Limitation

Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) with the following limitation: Operation of the A/C system is prohibited.
(p) Paperwork Reduction Act Burden
Statement

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200.
(q) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Wichita 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.

(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.

(r) Related Information

For more information about this AD, contact Craig Henrichsen, Aerospace Engineer, Electrical Systems and Avionics Branch, ACE–119W, FAA, Wichita ACO, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, KS 67209; phone: 316–946– 4110; fax: 316–946–4107; email: Craig.Henrichsen@faa.gov.
(s) 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) Subject 4–11–00, Replacement Time Limits, of Chapter 4, Airworthiness Limitations, Revision 6, dated June 23, 2014, of the Cessna Model 500/501 Maintenance Manual.

(ii) Subject 4–11–00, Replacement Time Limits, of Chapter 4, Airworthiness Limitations, Revision 10, dated June 23, 2014, of the Cessna Model 550/551 Maintenance Manual.

(iii) Subject 4–11–00, Replacement Time Limits, of Chapter 4, Airworthiness Limitations, Revision 12, dated June 23, 2014, of the Cessna Model 550 Bravo Maintenance Manual.

(iv) Subject 4–11–00, Replacement Time Limits, of Chapter 4, Airworthiness Limitations, Revision 9, dated June 23, 2014, of the Cessna Model S550 Maintenance Manual.

(v) Subject 4–11–00, Replacement Time Limits, of Chapter 4, Airworthiness Limitations, Revision 22, dated June 23, 2014, of the Cessna Model 560 Maintenance Manual.

(vi) Subject 4–11–00, Replacement Time Limits, of Chapter 4, Airworthiness Limitations, Revision 32, dated June 23, 2014, of the Cessna Model 650 Maintenance Manual.

(3) For service information identified in this AD, contact Cessna Aircraft Co., P.O. Box 7706, Wichita, KS 67277; phone: 316–517– 6215; fax: 316–517–5802; email: citationpubs@cessna.textron.com; Internet https://www.cessnasupport.com/ newlogin.html.

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

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

Issued in Renton, Washington, on August 10, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–20692 Filed 8–24–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–0242; Directorate Identifier 2014–NM–100–AD; Amendment**  **39–18240; AD 2015–17–07]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4–603, B4–605R, B4–620, B4–622, B4–622R airplanes; all Airbus Model A300 C4–605R Variant F airplanes; and certain Airbus Model A300 F4–605R airplanes. This AD was prompted by the manufacturer’s review of all repairs accomplished using the structural repair manual. This review was done using revised fatigue and damage tolerance calculations. This AD requires an inspection of the surrounding panels of the left and right forward passenger doors, and corrective actions if necessary. We are issuing this AD to detect and correct previous incomplete or inadequate repairs to the surrounding panels of the left and rightforward passenger doors and the failsafe ring, which could negatively affect the structural integrity of the airplane.

**DATES :**  This AD becomes effective September 29, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 29, 2015.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0242 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–


### 51448 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations

30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC.

For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet http://www.airbus.com. 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–

0242.

**FOR FURTHER INFORMATION CONTACT :**  Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149.

**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 all Airbus Model A300 B4–603, B4–605R, B4–620, B4–622, B4–622R airplanes; all Airbus Model A300 C4– 605R Variant F airplanes; and certain Airbus Model A300 F4–605R airplanes. The NPRM published in the Federal Register on February 18, 2015 (80 FR 8566).

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0101, dated May 2, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 B4–603, B4–605R, B4–620, B4–622, B4– 622R airplanes; all Airbus Model A300 C4–605R Variant F airplanes; and certain Airbus Model A300 F4–605R airplanes. The MCAI states:

In the frame of the Ageing Airplane Safety Rule (AASR), all existing Structural Repair Manual (SRM) repairs were reviewed.

This analysis, which consisted in new Fatigue and Damage Tolerance calculations, revealed that some repairs in the area surrounding the forward passenger/crew door and the fail safe ring are no longer adequate.

These repairs, if not reworked, could affect the structural integrity of the aeroplane.

To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A300– 53–6173 (later revised), to provide instructions for the inspection of repairs on the left-hand (LH) and right-hand (RH) forward door surrounding panels.

For the reasons described above, and further to the AASR implementation, this [EASA] AD requires a one-time inspection of the forward door surrounding panels to identify SRM repairs in these areas and, depending on findings, accomplishment of applicable corrective action(s).
Corrective actions include rework or repair.

You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2015-0242-

0002.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 8566, February 18, 2015) or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (80 FR 8566, February 18, 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 8566, February 18, 2015).

Related Service Information Under 1 CFR Part 51

Airbus has issued Service Bulletin A300–53–6173, Revision 01, dated February 28, 2014. The service information describes procedures for a one-time detailed of the area surrounding the forward passenger/crew door and the fail safe ring to determine if any repairs have been done, 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 of this AD.
Costs of Compliance

We estimate that this AD affects 65 airplanes of U.S. registry.

We also estimate that it will take about 120 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $663,000, or $10,200 per product. In addition, we estimate that any necessary follow-on actions will take up to 730 work-hours and require parts costing up to $72,250, for a cost of up to $134,300 per product. We have no way of determining the number of aircraft that might need these actions.
Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD:

1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866;

2. Is not a ‘‘significant rule’’ under the 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.
Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0242; 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


### 51449 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations

information. The street address for the Docket Operations office (telephone 800–647–5527) is in the **ADDRESSES** section.
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):

2015–17–07 Airbus: Amendment 39–18240. Docket No. FAA–2015–0242; Directorate Identifier 2014–NM–100–AD.

(a) Effective Date

This AD becomes effective September 29,

2015.
(b) Affected ADs

None.
(c) Applicability

This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.

(1) Model A300 B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes, all manufacturer serial numbers.

(2) Model A300 C4–605R Variant F airplanes, all manufacturer serial numbers.

(3) Model A300F4–605R airplanes, all manufacturer serial numbers, except those on which Airbus Modification 12699 was embodied in production.
(d) Subject

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

This AD was prompted by the manufacturer’s review of all repairs accomplished using the structural repair manual. This review was done using revised fatigue and damage tolerance calculations. We are issuing this AD to detect and correct previous incomplete or inadequate repairs to the surrounding panels of the left and right forward passenger doors and the fail-safe ring, which could negatively affect the structural integrity of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done. (g) Inspection At the time specified in paragraph (g)(1) or (g)(2) of this AD, whichever is later: Do a detailed inspection of the surrounding panels of the left and right forward passenger doors to determine if any repairs have been done, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6173, Revision 01, dated February 28,

2014.

(1) Prior to the accumulation of 30,000 total flight cycles or 67,500 total flight hours, whichever occurs first.

(2) Within 28 months after the effective date of this AD.
(h) Identification of Repairs

If any affected repair is found during the inspection required by paragraph (g) of this AD: Before further flight, identify the reworked area(s), the percentage of the rework, and the limits of the rework, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6173, Revision 01, dated February 28,

2014.
(i) Corrective Actions

During the repair identification required by paragraph (h) of this AD, if any rework is found that is outside the allowable damage limits specified in Airbus Service Bulletin A300–53–6173, Revision 01, dated February 28, 2014: Before further flight, rework or repair, as applicable, using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA).
(j) Exception to Service Information Specifications

Although Airbus Service Bulletin A300– 53–6173, Revision 01, dated February 28, 2014, specifies to contact Airbus for repair instructions, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; EASA; or Airbus’s EASA DOA.

(k) Credit for Previous Actions

This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–53–6173, dated August 1, 2013, which is not incorporated by reference in this AD.

(l) Other FAA AD Provisions

The following provisions also apply to this
AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Required for Compliance (RC): Except as required by paragraph (j) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of
an AMOC.

(3) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.

(m) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0101, dated May 2, 2014, for related information. This MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2015-0242-0002.

(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD.
(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 this AD specifies otherwise.

(i) Airbus Service Bulletin A300–53–6173, Revision 01, dated February 28, 2014.

(ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com.

(4) You may view this service information at the FAA, Transport Airplane Directorate,


### 51450 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations

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 August 10, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–20585 Filed 8–24–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0772; Directorate Identifier 2014–NM–090–AD; Amendment**  **39–18233; AD 2015–16–08]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding Airworthiness Directive (AD) 2011–08– 51 for certain The Boeing Company Model 737–300, –400, and –500 series airplanes. AD 2011–08–51 required repetitive inspections of the lap joint at certain stringers along the entire length from certain body stations. This new AD expands the inspection area, requires additional inspections for cracks and open pockets, requires corrective actions if necessary, and revises the compliance times. This AD was prompted by an evaluation by the design approval holder (DAH) that has determined that the lower fastener holes in the lower skin of the fuselage lap splice are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the lower fastener holes in the lower skin of the fuselage lap splice, which could result in reduced structural integrity of the airplane.

**DATES :**  This AD is effective September 29, 2015.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 29, 2015.

**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–

0772. 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– 0772; 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 to supersede AD 2011–08–51, Amendment 39–16701 (76 FR 28632, May 18, 2011). AD 2011–08–51 applied to certain The Boeing Company Model 737–300, –400, and –500 series airplanes. The NPRM published in the Federal Register on November 17, 2014 (79 FR 68381). The NPRM was prompted by an evaluation by the DAH that has determined that the lower fastener holes in the lower skin of the fuselage lap splice are subject to WFD. The NPRM proposed to continue to require repetitive inspections of the lap joint at certain stringers along the entire length from certain body stations. The NPRM also proposed to expand the inspection area, require additional inspections for cracks and open pockets, require corrective actions if necessary, and revise the compliance times. We are issuing this AD to detect and correct fatigue cracking of the lower fastener holes in the lower skin of the fuselage lap splice, which could result in reduced structural integrity of the airplane.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 68381, November 17, 2014) and the FAA’s response to each comment.
Request To Revise Wording

Boeing requested that we revise the last sentence in paragraph (k) of the proposed AD (79 FR 68381, November 17, 2014) to clarify that the on-condition actions may be ‘‘inspection or repair’’ rather than ‘‘inspection and repair.’’ Boeing stated that condition 10 in table 6 of Boeing Alert Service Bulletin 737– 53A1319, Revision 2, dated April 4, 2014, describes obtaining inspection or repair instructions. Boeing explained that, depending on the configuration details identified, repetitive inspections alone may be an appropriate action, or a repair may be the appropriate action.

We agree with the commenter’s request. Varying detail configurations and the total flight cycles at the time of the finding are used to determine if an inspection program is adequate to address the unsafe condition or if installation of a repair is required. We have revised the wording in paragraph (k) of this AD to require inspection or repair.
Request To Clarify Paragraph Heading

Southwest Airlines (SWA) stated that the heading ‘‘Repetitive Inspections for Crack Indications at Stringers S–4R and S–4L, Body Station (BS) 360 to BS 908,’’ of paragraph (g) of the proposed AD (79 FR 68381, November 17, 2014) is misleading. SWA explained that the heading is confusing since the paragraph contains both an initial inspection and repetitive inspections.

We agree to clarify the terminology used in the heading. When the term ‘‘repetitive’’ is used, it does not necessarily exclude the initial action. Many existing ADs use the term ‘‘repetitive’’ in the headers for paragraphs that contain both the initial action and repetitive actions. We find that no change to this AD is necessary regarding this issue.