### 36675 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules

(2) Do detailed and eddy current inspections of the frame at stations 328, 344, and 360 for cracking or a severed frame web; and external detailed and eddy current inspections of the fuselage skin for cracking.
(k) Group 7 Airplanes: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Station 328

For airplanes identified as Group 7 in Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013: At the applicable time specified in Table 6 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as provided by paragraph (m)(1) of this AD, do a detailed inspection of the frame at station 328 for cracking or a severed frame web; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections specified in this paragraph thereafter at the applicable time and intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013. Doing the repair of the frame at station 328, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, except as specified in paragraph (m)(2) of this AD, terminates the repetitive inspection requirements of this paragraph.
(l) Groups 2 Through 5 Airplanes: Repetitive Inspections, Related Investigative Actions, and Corrective Actions at Station 380

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

(1) Where Boeing Alert Service Bulletin 737–53A1323, dated December 6, 2013, specifies a compliance time after the ‘‘original issue date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

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

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

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

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization that has been authorized by the Manager, 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.
(p) Related Information

(1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6450; fax: 425–917–6590; email: alan.pohl@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 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 June 19,

2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–15251 Filed 6–27–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0345; Directorate Identifier 2013–NM–230–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Beechcraft Corporation (Type Certificate**  **Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft**  **Company; Beech Aircraft Corporation) 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 Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) Model 400, 400A, 400T, and MU–300 airplanes. This proposed AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). This proposed AD would require an inspection to determine if PTAs having a certain serial number and part number are installed, and replacement if they are installed. This proposed AD would also require repetitive replacements of PTAs with new PTAs or certain overhauled PTAs. We are proposing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane.

**DATES :**  We must receive comments on this proposed AD by August 29, 2014.

**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


### 36676 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules

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 Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201–0085; telephone 316–676–8238; fax 316–671–2540; email tmdc@beechcraft.com ; Internet http:// pubs.beechcraft.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–2014– 0345; 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 :**  Ann Johnson, Aerospace Engineer, Systems and Propulsion Branch, ACE–116W, FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, KS 67209; phone: (316) 946–4105; fax: (316) 946–4107; email: Ann.Johnson@ 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– 2014–0345; Directorate Identifier 2013– NM–230–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 a failure of the Acme nut threads in a PTA, due to accelerated thread wear on the Acme nut that mates with the jackscrew. This condition, if not corrected, could result in failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane.

Relevant Service Information

We reviewed Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012. This service bulletin describes procedures for an inspection to determine if PTAs having a certain serial number and part number are installed, and replacing those PTAs having specific serial numbers listed in the service bulletin.

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 these same type designs.
Proposed AD Requirements

This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between This Proposed AD and the Service Information.’’
Differences Between This Proposed AD and the Service Information

Although Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012, does not require repetitive replacements, this proposed AD would require repetitive replacements of PTAs with new PTAs or with overhauled PTAs having an Acme nut and jackscrew replaced with a new Acme nut and jackscrew every 1,800 flight hours or at the next PTA overhaul, whichever occurs first.

While the effectivity of Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012, does not include Model MU–300 airplanes, those airplanes are included in the applicability of this proposed AD since the affected PTAs can also be used on these airplanes.
Costs of Compliance

We estimate that this proposed AD affects 735 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

Identification of serial/part

numbers (735 airplanes). 1 work-hour × $85 per hour = $85. $0 ...................................... $85 .................................... $62,475.

Replacement of PTA (26

airplanes). 10 work-hours × $85 perhour = $850 per replacement. $17,334 per replacement .. $18,184 per replacement .. $472,784 per replacement.

Repetitive replacement of

jackscrew and Acme nut on PTAs (735 airplanes). 10 work-hours × $85 perhour = $850 per replacement. $17,334 per replacement .. $18,184 per replacement .. $13,365,240 per replacement.

According to the manufacturer, the costs of this proposed AD associated with Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012, may be covered under warranty, thereby reducing the cost impact on affected owners/operators. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. The costs of the repetitive replacement are not covered under warranty. However, the PTA manufacturer states that it is already replacing the Acme nut and jackscrew at every overhaul, so the owners/operators should not see a cost increase due to this repetitive replacement requirement.


### 36677 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules

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 proposed 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):
Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation): Docket No. FAA–2014–0345; Directorate Identifier 2013–NM–230–AD.

(a) Comments Due Date

We must receive comments by August 29,

2014.
(b) Affected ADs

None.
(c) Applicability

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

(1) Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Beech Aircraft Corporation) airplanes identified in paragraphs (c)(1)(i), (c)(1)(ii), and (c)(1)(iii) of this AD.

(i) Model 400 Beechjet airplanes having serial numbers RJ–1 through RJ–65, inclusive.

(ii) Model 400A Beechjet airplanes having serial numbers RK–1 through RK–604, inclusive.

(iii) Model 400T Beechjet airplanes having serial numbers TT–1 through TT–180, inclusive, and TX–1 through TX–13, inclusive.

(2) Beechcraft Corporation (Type Certificate Previously Held by Hawker Beechcraft Corporation; Raytheon Aircraft Company; Mitsubishi Heavy Industries, Inc. Ltd.) Model MU–300 airplanes, having serial numbers A003SA through A093SA, inclusive.
(d) Subject

Air Transport Association (ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

This AD was prompted by a report of a failure of the Acme nut threads in a pitch trim actuator (PTA). We are issuing this AD to prevent failure of the Acme nut threads in the PTA, which could lead to loss of control of pitch trim and reduced controllability of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Determination of Serial Number and Part Number

Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, inspect to determine the serial number and part number of the PTA, in accordance with the Accomplishment Instructions of Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012. A review of manufacturer delivery and operator maintenance records is acceptable, in lieu of the inspection, if the serial number and part number of the PTA can be conclusively determined from that review.
(h) Replacement

If any serial number and part number found during an inspection required by paragraph (g) of this AD is one listed in Table 1 or Table 2 of Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012: Within 200 flight hours or 6 months after the effective date of this AD, whichever occurs first, replace the PTA with a serviceable PTA or an overhauled PTA having an Acme nut and jackscrew replaced with a new Acme nut and jackscrew, in accordance with the Accomplishment Instructions of Hawker Beechcraft Mandatory Service Bulletin 27– 4100, dated March 2012.
(i) Repetitive Replacements

Within 1,800 flight hours after the effective date of this AD, or at the next PTA overhaul, whichever occurs first, replace the PTA with a new PTA or an overhauled PTA having the Acme nut and jackscrew replaced with a new Acme nut and jackscrew, in accordance with sections 3.A.(2), (3), and (5) through (10) of Hawker Beechcraft Mandatory Service Bulletin 27–4100, dated March 2012. Repeat the replacement thereafter at intervals not to exceed 1,800 flight hours, or at every PTA overhaul, whichever occurs first.
(j) 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 (k)(1) 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.

(k) Related Information

(1) For more information about this AD, contact Ann Johnson, Aerospace Engineer, Systems and Propulsion Branch, ACE–116W, FAA, Wichita Aircraft Certification Office(ACO), 1801 Airport Road, Room 100, MidContinent Airport, Wichita, KS 67209; phone: (316) 946–4105; fax: (316) 946–4107; email: Ann.Johnson@faa.gov.

(2) For service information identified in this AD, contact Beechcraft Corporation, TMDC, P.O. Box 85, Wichita, KS 67201– 0085; telephone 316–676–8238; fax 316–671– 2540; email tmdc@beechcraft.com; Internet http://pubs.beechcraft.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.


### 36678 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules

Issued in Renton, Washington, on June 10,

2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–15246 Filed 6–27–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0426; Directorate Identifier 2013–NM–231–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 and 777 airplanes. This proposed AD was prompted by reports of uncommanded door closure of the large lower lobe cargo door. This proposed AD would require inspecting for part numbers and serial numbers of the rotary actuators of the large forward and aft lower lobe cargo doors, as applicable, and corrective action if necessary. We are proposing this AD to detect and correct rotary actuators made with a material having poor actuator gear wear characteristics, which could result in failure of the rotary actuators for the large forward or aft lower lobe cargo door and subsequent uncommanded door closure, which could possibly result in injury to people on the ground.

**DATES :**  We must receive comments on this proposed AD by August 14, 2014.

**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 Boeing 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. For Eaton service information identified in this proposed AD, contact Eaton Corporation, Aerospace Operations, 3 Park Plaza, Suite 1200, Irvine, CA 92614; telephone 949–253–2100; fax 949–253–2111; Internet http://
www.eaton.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–2014– 0426; 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 :**  Susan Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6457; fax: 425–917–6590; email: susan.l.monroe@ 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– 2014–0426; Directorate Identifier 2013– NM–231–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 uncommanded door closure of the large lower lobe cargo door. One incident occurred while the door was being opened, a second one while the door was stationary in the open position, and the third incident occurred as the door was being closed. It was determined that all of the doors’ rotary actuators had failed (two actuators per door). The three incidents occurred on Model 767 airplanes, but the same rotary actuator part numbers are also used on the large lower lobe cargo doors installed on the Model 777 airplanes. Examination of five of the failed rotary actuators found significant wear in the gear box and failure of the first stage input sun gear set. The sixthfailed rotary actuator had a failed thirdstage input sun gear from an overload condition. All three affected airplanes had between 12,500 and 13,500 total flight cycles. The failed actuators were manufactured with Nitralloy 135M steel between August 1994 and December 2000. Actuators manufactured before or after that timeframe were made with 9310 steel. The rotary actuators made from 9310 steel material are considered safe. This condition, if not corrected, could result in failure of the rotary actuators for the large lower lobe cargo door, and subsequent uncommanded door closures, which could possibly result in injury to people on the ground.

Relevant Service Information

We reviewed Boeing Service Bulletins 767–52A0100, Revision 2, dated September 26, 2013; and 777–52–0053, Revision 1, dated September 26, 2013. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014–

0426.

Boeing Service Bulletins 767– 52A0100, Revision 2, dated September 26, 2013; and 777–52–0053, Revision 1, dated September 26, 2013; refer to Eaton Service Bulletin 692D100–52–4, Revision 2, dated August 1, 2013, which provides serial number information and certain corrective actions (rework of certain rotary actuators or reidentification of certain other rotary actuators).

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