### 32063 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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):
The Boeing Company: Docket No. FAA– 2015–1423; Directorate Identifier 2014– NM–173–AD.
(a) Comments Due Date

We must receive comments by July 20,
2015.
(b) Affected ADs

None. (c) Applicability

This AD applies to The Boeing Company Model 757–200 series airplanes modified by the applicable supplemental type certificate identified in paragraphs (c)(1) and (c)(2) of this AD.

(1) ST01529SE ( http://rgl.faa.gov/ Regulatory

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_Library/rgstc.nsf/ 0/0AF09C3701A237EE86257A5D0064B3AA? OpenDocument&Highlight=st01529se ).

(2) ST02278SE ( http://rgl.faa.gov/ Regulatory

_ and

_ Guidance

_Library/rgstc.nsf/ 0/E54B5289A2E9F6EF86257B7F0056EDAF? OpenDocument&Highlight=st02278se ).
(d) Subject

Air Transport Association (ATA) of America Code 11, Placards and Markings.

(e) Unsafe Condition

This AD was prompted by reports of a main cargo door being blown past its full open position while on the ground during gusty wind conditions, which resulted in uncontrolled fall down to its closed position. We are issuing this AD to prevent damage to the main cargo door, which could result in rapid decompression, leading to in-flight breakup.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Installation

Within 90 days after the effective date of this AD, install a new placard and bracket, replace the existing placard, and replace the main cargo door control panel, in accordance with the Accomplishment Instructions of Precision Conversions LLC Service Bulletin PC–757–11–0023, dated August 1, 2014.
(h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (i)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.
(i) Related Information

(1) For more information about this AD, contact Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM 120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6513; fax: 425–917–6590; email: Narinder.Luthra@faa.gov.

(2) For service information identified in this AD, contact Precision Conversions LLC, 4900 SW Griffith Drive, Suite 133, Beaverton, OR 97005; ATTN: Steven A. Lopez; phone: 503–601–3001; email: Steven.Lopez@ precisionaircraft.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.

Issued in Renton, Washington, on May 18,
2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015–13358 Filed 6–4–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1422; Directorate Identifier 2014–NM–125–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to supersede Airworthiness Directive (AD) 98–18–26, for certain Airbus Model A320 series airplanes. AD 98–18–26 currently requires repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings; and repair, if necessary. Since we issued AD 98–18– 26, we have received reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. This proposed AD would require repetitive high frequency eddy current (HFEC) inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, and a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe.

**DATES :**  We must receive comments on this proposed AD by July 20, 2015.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Airbus, Airworthiness Office—EIAS, 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. 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– 1422; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday,


### 32064 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules

except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2015–1422; Directorate Identifier 2014–NM–125–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD.

Discussion

On August 28, 1998, we issued AD 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998). AD 98– 18–26 requires repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe on certain Airbus Model A320 series airplanes. AD 98–18–26 contains a modification that provides a terminating action for the repetitive inspection requirements.

Since we issued AD 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998), we have received reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes where shims were installed under the heads of 2 fasteners at the top end of the front spar vertical stringers using Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57–1017, Revision 01, dated March 17, 1997, or on which modification 21290P1546 was accomplished during production.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0069, dated March 19, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on certain Airbus Model A320–211, –212, and –231 airplanes. The MCAI states:

During center fuselage certification full scale fatigue test, cracks were found on the front vertical stringer at frame 36. Analysis ofthese findings indicated that a number of inservice aeroplanes could be similarly affected.

This condition, if not detected and corrected, could lead to crack propagation and consequent deterioration of the structural integrity of the aeroplane.

To address this potential unsafe condition, [Directorate General for Civil Aviation] DGAC France AD 97–311–105 [which corresponds to FAA AD 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998)] was issued to require repetitive [HFEC] inspections [for cracking] in accordance with the instruction of Airbus Service Bulletin (SB) A320–57–1016. At the same time, the modification provided by Airbus SB A320–57–1017 was considered to be terminating action for the repetitive inspections required by DGAC France AD
97–311–105.

Since that [DGAC] AD was issued, and following new analysis, modification per Airbus SB A320–57–1017 is no longer considered to be terminating action for the repetitive inspections as required by DGAC France AD 97–311–105.

Aeroplanes with [manufacturer serial number] MSN 0080 up to 0155 inclusive have been delivered with the addition of a 5 [millimeter] mm thick light alloy shim under the heads of 2 fasteners at the top end of the front spar vertical stringers (Airbus modification 21290P1546, which is the production line equivalent to in-service modification through Airbus SB A320–57– 1017). From MSN 0156 and higher, all aeroplanes are delivered with vertical stiffeners of the forward wing spar upper end with stiffener cap thickness increased from 4 to 6 mm (Airbus modification 21290P1547).

Prompted by these findings, Airbus issued SB A320–57–1178 to introduce new repetitive inspections with new thresholds and intervals.

For the reasons described above, DGAC France AD 97–311–105 is superseded and this [EASA] AD requires the repetitive inspections at new thresholds and intervals.

After EASA issued [proposed airworthiness directive] PAD 14–021, it was discovered that additional work [HFEC inspections for cracking of the radius of spar vertical stringers and horizontal beam in the center fuselage of frame 36, and a rototest inspection for cracking of the fastener holes of the spar vertical stringers radius on Frame 36 and repair if necessary], to be included in Revision 01 of Airbus SB A320–57–1178, is required to accomplish the inspections. This Final [EASA] AD has been amended accordingly. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–
1422.

Related Service Information Under 1 CFR Part 51

Airbus has issued Service Bulletin A320–57–1178, Revision 01, including Appendix 01, dated May 28, 2014. The service information describes procedures for inspecting the radius of the front spar vertical stringers and the horizontal floor beam on frame 36 for cracking. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 NPRM. FAA’s Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information

Although EASA AD 2014–0069, dated March 19, 2014, specifies to accomplish an HFEC inspection for cracking of the vertical stiffeners radius, this proposed AD would require accomplishing an HFEC inspection for cracking of the radius of the front spar vertical stringers, since Airbus Service Bulletin A320–57–1178, Revision 01, Appendix 01, dated May 28, 2014, specifies the inspection is of the front spar vertical stringers. Costs of Compliance

We estimate that this proposed AD affects 17 airplanes of U.S. registry.

We also estimate that it would take about 24 work-hours per product to comply with the basic requirements of this proposed AD. The average labor


### 32065 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules

rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $34,680, or $2,040 per product.

In addition, we estimate that any necessary follow-on actions would take about 49 work-hours and require parts costing $1,210, for a cost of $5,375 per product. We have no way of determining the number of aircraft that might need this action. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:

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. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998), and adding the following new AD:

Airbus: Docket No. FAA–2015–1422; Directorate Identifier 2014–NM–125–AD.

(a) Comments Due Date

We must receive comments by July 20,
2015.
(b) Affected ADs

This AD replaces AD 98–18–26, Amendment 39–10742 (63 FR 47423, September 8, 1998).
(c) Applicability

This AD applies to Airbus Model A320– 211, –212, and –231 airplanes, certificated in any category, manufacturer serial numbers 0001 through 0155 inclusive.
(d) Subject

Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

This AD was prompted by cracks found on the front vertical stringer at frame 36. This AD was also prompted by reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. We are issuing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Inspections

Within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, and do a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–57–1178, Revision 01, including Appendix 01, dated May 28, 2014. Repeat the inspections thereafter at the compliance times specified in paragraphs (g)(1) and (g)(2) of this AD.

(1) For Configuration 1 airplanes identified in paragraph (h)(1) of this AD: At intervals not to exceed 8,800 flight cycles or 17,700 flight hours, whichever occurs first.

(2) For Configuration 2, 3, and 4 airplanes identified in paragraphs (h)(2) through (h)(4) of this AD: At intervals not to exceed 24,900 flight cycles or 49,800 flight hours, whichever occurs first.
(h) Compliance Times for Initial Inspections Required by Paragraph (g) of This AD

Do the initial inspections required by paragraph (g) of this AD within the applicable compliance times specified in paragraphs (h)(1) through (h)(4) of this AD.

(1) For Configuration 1 airplanes, having manufacturer serial number (MSN) 0001 though MSN 0079 inclusive, on which the modification specified by Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57– 1017, Revision 01, dated March 17, 1997, has not been accomplished: At the later of the times specified by paragraphs (h)(1)(i) through (h)(1)(iii) of this AD:

(i) The later of the times specified by paragraphs (h)(1)(i)(A) and (h)(1)(i)(B) of this AD:

(A) Within 24,000 flight cycles or 48,000 flight hours, whichever occurs first since airplane first flight.

(B) Within 60 days after the effective date of this AD.

(ii) Within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the last inspection specified in Airbus Service Bulletin A320–57–1016 was accomplished.

(iii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD, without exceeding 14,000 flight cycles after the last inspection specified in Airbus Service Bulletin A320– 57–1016 was accomplished.

(2) For Configuration 2 airplanes, having MSN 0001 to 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320–57–1016, have not been done prior to accomplishing the actions specified by Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57–1017, Revision 01, dated March 17, 1997: At the later of the times specified by paragraphs (h)(2)(i) and (h)(2)(ii) of this AD:

(i) Within 8,800 flight cycles or 17,700 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57– 1017, Revision 01, dated December 6, 1995, was accomplished.

(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.

(3) For Configuration 3 airplanes, having MSN 0001 to 0079 inclusive, on which the actions specified by Airbus Service Bulletin A320–57–1016, have been done prior to accomplishing the actions specified by Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57–1017, Revision 01, dated


### 32066 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules

March 17, 1997: At the later of the times specified by paragraphs (h)(3)(i) and (h)(3)(ii) of this AD:

(i) Within 24,900 flight cycles or 49,800 flight hours, whichever occurs first, since the modification specified in Airbus Service Bulletin A320–57–1017, dated September 3, 1991; or Airbus Service Bulletin A320–57– 1017, Revision 01, dated March 17, 1997, was accomplished.

(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.

(4) For Configuration 4 airplanes, having MSN 0080 to 0155 inclusive:

At the later of the times specified in paragraphs (h)(4)(i) or (h)(4)(ii) of this AD:

(i) Before exceeding 54,300 flight cycles or 108,600 flight hours, whichever occurs first since airplane first flight.

(ii) Within 60 days after the effective date of this AD.
(i) Repair

If any crack is detected during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA).
(j) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116- AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD.

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

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0069, dated March 19, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–
2015–1422.

(2) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 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 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.

Issued in Renton, Washington, on May 18,
2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–13342 Filed 6–4–15; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2015–1421; Directorate Identifier 2014–NM–177–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

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

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 767–300 and –300F series airplanes. This proposed AD was prompted by reports of fatigue cracking on airplanes with Aviation Partners Boeing winglets installed. This proposed AD would require a high frequency eddy current (HFEC) inspection for cracking of the lower outboard wing skin, and repair or modification if necessary. This proposed AD would also require one of three follow-on actions: Repeating the HFEC inspections; modifying certain internal stringers and oversizing and plugging the existing fastener holes of the lower wing; or modifying the external doubler/tripler and doing repetitive post-modification inspections. We are proposing this AD to prevent fatigue cracking in the lower outboard wing skin, which could result in failure and subsequent separation of the wing and winglet and consequent reduced controllability of the airplane.

**DATES :**  We must receive comments on this proposed AD by July 20, 2015.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Aviation Partners Boeing, 2811 S. 102nd Street, Suite 200, Seattle, WA 98168; telephone 206–762–1171; Internet https:// www.aviationpartnersboeing.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. 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– 1421; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6487; fax: 425–917–6590; email: Allen.Rauschendorfer@faa.gov

. **SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2015–1421; Directorate Identifier 2014– NM–177–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the