### 46540 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules

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 adding the following new airworthiness directive (AD):
The Boeing Company: Docket No. FAA– 2013–0666; Directorate Identifier 2013– NM–060–AD.
(a) Comments Due Date

We must receive comments by September 16, 2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to all The Boeing Company Model 727, 727C, 727–100, 727 –100C, 727–200, and 727–200F series airplanes; certificated in any category.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition

This AD was prompted by reports indicating that a standard fuel tank access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. We are issuing this AD to prevent foreign object penetration of the fuel tank, which could cause a fuel leak near an ignition source (e.g., hot brakes), consequently leading to a fuel-fed fire.
(f) Compliance

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

Within 72 months after the effective date of this AD, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727– 28–0134, dated January 12, 2012.

(1) Do either a general visual inspection or ultrasonic non-destructive test of the left- and right-hand wing fuel tank access doors to determine whether impact-resistant access doors are installed in the correct locations. If any standard access door is found, beforefurther flight, replace with an impactresistant access door, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727–28–0134, dated January 12, 2012.

(2) Do a general visual inspection of theleft- and right-hand wing fuel tank impactresistant access doors to verify stencils and index markers are applied. If a stencil or index marker is missing, before further flight, apply stencil or index marker, as applicable, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727– 28–0134, dated January 12, 2012.
(h) Maintenance Program Revision

Within 60 days after the effective date of this AD, revise the maintenance program to incorporate Critical Design Configuration Control Limitation (CDCCL) Task 57–AWL– 01, ‘‘Impact-Resistant Fuel Tank Access Door,’’ of Section 1, Airworthiness Limitations (AWLs) of Boeing 727–100/200 Airworthiness Limitations (AWLs) Document D6–8766–AWL, Revision September 2012.

(i) No Alternative CDCCLs

After accomplishing the revision required by paragraph (h) of this AD, no alternative CDCCLs may be used unless the CDCCLs are approved as an alternative method of compliance in accordance with the procedures specified in paragraph (j) of this AD.
(j) 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 (ODA) that has been authorized by the Manager, Seattle 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. (k) Related Information (1) For more information about this AD, contact Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6438; fax: 425–917–6590; email: suzanne.lucier@faa.gov.

(2) 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 review copies of the 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 July 21,
2013. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–18507 Filed 7–31–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0667; Directorate Identifier 2013–NM–062–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 747–400 airplanes. This proposed AD was prompted by reports of fasteners missing on an airplane undergoing a passenger-to-freighter conversion. This proposed AD would require doing a general visual inspection of the station 1920 splice clip for correct fastener installation, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct missing or incorrect fasteners, which can lead to cracking and loss of load carrying capacity, resulting in a possible decompression event.

**DATES :**  We must receive comments on this proposed AD by September 16,
2013.

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


### 46541 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules

• 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 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 review copies of the 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; 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 :**  Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917– 6590; email: bill.ashforth@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– 2013–0667; Directorate Identifier 2013– NM–062–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 have received a report of anairplane, while undergoing a passengerto-freighter conversion, missing fasteners on the station 1920 splice clip. The possibility of this discrepancy exists on airplanes already delivered. This condition, if not corrected, could result in cracking and loss of load carrying capacity, resulting in a possible decompression event.

Relevant Service Information

We reviewed Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for Docket No. FAA–2013–0667. 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, except as discussed under ‘‘Differences Between the Proposed AD and the Service Information.’’

The phrase ‘‘related investigative actions’’ might be used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that: (1) Are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections.

In addition, the phrase ‘‘corrective actions’’ might be used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between the Proposed AD and the Service Information

Although the service bulletin specifies that operators may contact the manufacturer for disposition of certain repair conditions, this proposed AD would require operators to repair those conditions in accordance with a method approved by the FAA. Costs of Compliance

We estimate that this proposed AD affects 3 airplanes of U.S. registry.

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



### E STIMATED 

### COSTS

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

Inspection for correct fastener installation ............ 2 work-hours × $85 per hour = $170 ................... $0 $170 $510

We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs:



### O N 

### -CONDITION 

### COSTS

Action Labor cost Parts cost Cost per product

Inspections for cracking .................................................... 3 work-hours × $85 per hour = $255 ............................... $0 $255
Fastener installation .......................................................... 2 work-hours × $85 per hour = $170 ............................... 0 170 Repair ................................................................................ 2 work-hours × $85 per hour = $170 ............................... 0 170


### 46542 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules

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. 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– 2013–0667; Directorate Identifier 2013– NM–062–AD.
(a) Comments Due Date

We must receive comments by September 16, 2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to The Boeing Company Model 747–400 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by reports of fasteners missing on an airplane undergoing a passenger-to-freighter conversion. We are issuing this AD to detect and correct missing or incorrect fasteners, which can lead to cracking and loss of load carrying capacity, resulting in a possible decompression event.
(f) Compliance

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

Except as required by paragraph (h)(1) of this AD, at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012: Do a general visual inspection for correct installation of the station 1920 splice clip common to the auxiliary sill web and the tie clip, and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012, except as required by paragraph (h)(2) of this AD. Do all applicable related investigative and corrective actions before further flight.
(h) Exceptions to the Service Information

(1) Where Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012, specifies a compliance time ‘‘after the original issue date of the 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 747–53A2844, Revision 1, dated July 30, 2012, specifies contacting Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(i) Credit for Previous Actions

This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2844, dated September 15, 2011, except the detailed inspection for cracking of the auxiliary sill outer chord tee and attached parts and all applicable related investigative and corrective actions must be done in accordance with Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012, at the times specified in paragraph (g) of this AD. Boeing Alert Service Bulletin 747–53A2844, dated September 15, 2011, is not incorporated by reference in this AD. (j) 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 (ODA) that has been authorized by the Manager, Seattle 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.
(k) Related Information

(1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: bill.ashforth@faa.gov.

(2) 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 review copies of the referenced service information at the FAA, Transport Airplane


### 46543 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules

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 July 21,
2013. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–18564 Filed 7–31–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0665; Directorate Identifier 2012–NM–082–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Airplanes** 

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330–300 series airplanes and Model A340–200 and –300 series airplanes. This proposed AD was prompted by reports of corrosion found on certain trimmable horizontal stabilizer actuators (THSA), affecting the ballscrew lower splines between the tie bar and the screw-jack. This proposed AD would require repetitive detailed inspections for corrosion of certain THSAs, ballscrew integrity tests if necessary; and replacing any affected THSA with a serviceable or new and improved THSA, if necessary. We are proposing this AD to detect and correct corrosion of the THSAs, which could lead, in the case of ballscrew rupture, to the loss of transmission of THSA torque loads from the ballscrew to the tie-bar, prompting THSA blowback, and possibly resulting in loss of control of the airplane.

**DATES :**  We must receive comments on this proposed AD by September 16,
2013.

**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 Airbus service information identified in this proposed AD, contact Airbus SAS—Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330- A340@airbus.com; Internet http:// www.airbus.com . For Goodrich service information identified in this proposed AD, contact Goodrich Corporation, Actuation Systems, Product Support Department 13, Avenue de L’Eguillette—Saint-Ouen L’Aumone Boite Postale 7186 95056, Cergy Pontoise Cedex, France; fax: 33–1– 34326310. You may review copies of the 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; or in person at the Docket Operations office 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 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 :**  Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1138; 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–2013–0665; Directorate Identifier 2012–NM–082–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

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0061R1, dated November 30, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

Some Trimmable Horizontal Stabilizer Actuators (THSA), Part Number (P/N) 47147– 500, have been found with corrosion, affecting the ballscrew lower splines between the tie bar and the screw-jack.

The results of the technical investigations have identified that the corrosion was caused by a combination of:
—Contact/friction between the tie bar and the

inner surface of the ballscrew leading to the removal of Molykote (corrosion protection) at the level of the tie bar splines, —Humidity ingress initiating surface

oxidation starting from areas where Molykote is removed, and —Water retention in THSA lower part

leading to corrosion spread out and to the creation of a brown deposit (iron oxide). The results of the technical investigations have also concluded that THSA P/N 47147– 500 and P/N 47147–700 ballscrews might be affected by this corrosion issue.

THSA P/N 47147–400 ballscrews might be affected as well, but should no longer be in service, and modified into P/N 47147–500, as required by EASA AD 2010–0192 and EASA AD 2010–0193 [and as required by FAA AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005)].

This condition, if not detected and corrected, may lead, in case of ballscrew rupture, to loss of transmission of THSA torque loads from the ballscrew to the tie-bar, prompting THSA blowback, possibly resulting in loss of control of the aeroplane.

To correct this potential unsafe condition, EASA issued AD 2012–0061 to require repetitive [detailed] visual inspections of the ballscrew lower splines of THSA having P/N 47147–500 or P/N 47147–700 to detect corrosion and, depending on findings [ballscrew integrity tests], the accomplishment of applicable corrective actions [replacing the affected THSA with a serviceable or improved THSA].

Since that [EASA] AD [2012–0061] was issued, Airbus published new Service Bulletin (SB) A330–27–3194 or Airbus SB A340–27–4187 (Airbus modification 202802), which allow installation in service of an improved THSA P/N 47172–530.

For the reasons described above, this [EASA] AD [2012–0061R1] is revised to specify that installation of THSA P/N 47172–