### 32061 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules

(l) New Requirement of This AD: Repetitive Inspections for Certain Airplanes

Repeat the inspection specified in paragraph (k) of this AD thereafter at the applicable interval specified in paragraphs (l)(1) and (l)(2) of this AD.

(1) For airplanes whose flight time average is equal to or more than 1.5 hours, at intervals not to exceed 8,500 flight cycles or 18,500 flight hours, whichever occurs first.

(2) For airplanes whose flight time average is less than 1.5 hours, at intervals not to exceed 9,200 flight cycles or 13,700 flight hours, whichever occurs first.
(m) New Requirement of This AD: Corrective Actions

(1) If any cracking is detected or suspected during any detailed visual inspection required by paragraph (i) or (j) of this AD: Before further flight, confirm this finding and the length of this cracking by conducting an HFEC inspection, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6044, Revision 04, including Appendix 01, dated August 19, 2011, except as specified in paragraph (o) of this AD. If no cracking is confirmed during the HFEC inspection, accomplish the applicable repetitive inspections required by paragraphs (j) and (l) of this AD at the applicable time specified in those paragraphs.

(2) If any cracking is found during any HFEC inspection required by paragraph (i), (j), (k) or (l) of this AD: Before further flight, do the applicable actions specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.

(i) If the cracking is 75 mm or less per each rib bay: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6044, Revision 04, including Appendix 01, dated August 19, 2011, except as specified in paragraph (o) of this AD. Do repetitive detailed visual inspections of the repaired area thereafter at intervals not to exceed 50 flight cycles or 110 flight hours, whichever occurs first, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–6044, Revision 04, including Appendix 01, dated August 19, 2011. Within 250 flight cycles or 550 flight hours, whichever occurs first after doing the temporary repair, do a permanent repair of the repaired area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–6044, Revision 04, including Appendix 01, dated August 19, 2011.

(ii) If the cracking exceeds 75 mm per any rib bay: Before further flight, install Airbus Modification 10089, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6044, Revision 04, including Appendix 01, dated August 19, 2011. Do an LFEC inspection thereafter at the intervals specified in paragraph (l) of this AD.

(3) If any cracking is found during any inspection required by this AD at fastener holes 1A, 1, or 2: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6044, Revision 04, including Appendix 01, dated August 19,
2011. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (i) through (l) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–57–6044, Revision 03, dated April 7, 1999, including Appendix 01, which is not incorporated by reference in this AD. (o) Exception to Service Information Specification

Although Airbus Service Bulletin A300– 57–6044, Revision 04, including Appendix 01, dated August 19, 2011, specifies to submit information to Airbus, this AD does not require that submission.
(p) 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) 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
(q) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0221, dated September 19, 2013, 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–2015–1426.

(2) 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 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 19,
2015. Dionne Palmero, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2015–13335 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–2015–1423; Directorate Identifier 2014–NM–173–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 757–200 Series**  **Airplanes Modified by Supplemental Type Certificate (STC) ST01529SE or**  **STC ST02278SE**

**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 757–200 series airplanes modified by particular STCs. This proposed 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. This proposed AD would require installing a new placard and bracket, replacement of an existing placard, and replacement of the main cargo door control panel. We are proposing this AD to prevent damage to the main cargo door, which could resultin rapid decompression, leading to inflight breakup.

**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 Precision


### 32062 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules

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.
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– 1423; 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 :**  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

.
**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– 2015–1423; Directorate Identifier 2014– NM–173–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 because of 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

We received reports of a main cargo door being blown past its full open position during gusty wind conditions, resulting in a subsequent uncontrolled fall down to its closed position. It was determined that the Precision Conversions freighter conversion installs a main cargo door that, in certain wind conditions, can rotate open past the full-open position. This can result in damage to the door and surrounding structure, which can go unnoticed by the crew. If a damaged airplane takes off and is pressurized per normal procedures the cargo door could fail. This condition, if not corrected, could result in rapid decompression, leading to in-flight breakup.

Related Service Information Under 1 CFR Part 51

We reviewed Precision Conversions LLC Service Bulletin PC–757–11–0023, dated August 1, 2014. The service information describes procedures for installing a new placard and bracket, replacement of an existing placard, and replacement of the main cargo door control panel. 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

We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements

This proposed AD would require accomplishing the actions specified in the service information described previously. Costs of Compliance

We estimate that this proposed AD affects 9 airplanes of U.S. registry.

We estimate the following costs to comply with this proposed AD:



### E STIMATED 

### C OSTS

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

Installation ............................... 6 work-hours × $85 per hour = $510 ..................................... $0 $510 $4,590

According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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.


### 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

_ and

_ Guidance

_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,