### 68384 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules

(g) Repetitive Inspections for Crack Indications at Stringers S–4R and S–4L, Body Station (BS) 360 to BS 908

At the applicable time specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014: Do an external eddy current inspection, or internal eddy current and detailed inspections, for crack indications at stringers S–4R and S–4L, from body station (BS) 360 to BS 908, except as provided by paragraph (h) of this AD, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014. Repeat the inspection(s) thereafter at the applicable intervals specified in Table 1 or Table 2, as applicable, of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014. Either inspection option may be used at any repetitive inspection cycle.
(h) One-Time Inspections for Cracks at Stringers S–4L and S–4R, BS 360 to BS 908

At the applicable time specified in Table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD: Do one-time internal detailed and eddy current inspections for cracks at stringers S–4R and S–4L, from BS 360 to BS 908, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014. Accomplishment of the inspections required by this paragraph does not terminate the repetitive inspections required by paragraph (g) of this AD.
(i) One-Time Inspections for Cracks at Stringer S–4R, BS 908 to BS 1016

For airplanes identified as Group 2, 3, 5, and 7 in Boeing Alert Service Bulletin 737– 53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in Table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014, except asrequired by paragraph (m) of this AD, do onetime internal detailed and eddy current inspections for cracks at stringer S–4R, from BS 908 to BS 1016, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014.
(j) Repetitive Inspections for Cracks at Stringer S–4R, BS 908 to BS 1016

For airplanes identified as Group 2, 3, 5, and 7 in Boeing Alert Service Bulletin 737– 53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in Table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD, do external eddy current inspections, or internal eddy current and detailed inspections, for cracks at stringer S–4R, from BS 908 to BS 1016, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014. Repeat the inspection(s) thereafter at the applicable intervals specified in Table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1319, Revision 2, dated April 4, 2014. Either inspection option may be used at any repetitive inspection cycle.
(k) General Visual Inspection for Open Pockets at Stringer S–4R, BS 908 to BS 1016

For airplanes identified as Group 1, 4, and 6 in Boeing Alert Service Bulletin 737– 53A1319, Revision 2, dated April 4, 2014: At the applicable time specified in Table 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014, except as required by paragraph (m) of this AD, do a general visual inspection for open pockets of the lower skin panel at stringer S–4R, from BS 908 to BS 1016, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1319, Revision 2, dated April 4, 2014. If any open pocket is found, before further flight, inspect and repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD.

(l) Corrective Action

If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (o) of this AD. Accomplishment of repairs approved in accordance with the procedures specified in paragraph (o) of this AD terminates the repetitive inspections specified in paragraphs (g) and (j) of this AD in the repaired areas only.
(m) Service Information Exception

Where Boeing Alert Service Bulletin 737– 53A1319, Revision 2, dated April 4, 2014, specifies a compliance time ‘‘after the Revision 2 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

(n) 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 737–53A1319, dated April 4, 2011; or Boeing Alert Service Bulletin 737– 53A1319, Revision 1, dated April 8, 2011. Boeing Alert Service Bulletin 737–53A1319, dated April 4, 2011, is incorporated by reference in AD 2011–08–51, Amendment 39–16701 (76 FR 28632, May 18, 2011). Boeing Alert Service Bulletin 737–53A1319, Revision 1, dated April 8, is not incorporated by reference in 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 (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.

(4) AMOCs approved for AD 2011–08–51, Amendment 39–16701 (76 FR 28632, May 18, 2011), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (l) of this AD.
(p) Related Information

(1) For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6447; fax: 425–917–6590; email: wayne.lockett@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 November 5, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–27070 Filed 11–14–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0773; Directorate Identifier 2014–NM–068–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 all The Boeing Company Model 787–8


### 68385 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules

airplanes. This proposed AD was prompted by reports of a potential latent failure of the valve actuator circuitry, which was not identified during actuator development. This proposed AD would require replacing certain engine and auxiliary power unit (APU) fuel shutoff valve actuators with new actuators, and would also require revising the maintenance or inspection program to include a new airworthiness limitation into the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA). We are proposing this AD to prevent latent failures of the fuel shutoff valve actuators, which could result in the inability to shut off fuel to the engine or APU in the case of an engine or APU fire. If the fuel cannot be shut off to a fire, the engine or APU fire could be uncontrollable, which could lead to structural failure.

**DATES :**  We must receive comments on this proposed AD by January 2, 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 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.
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– 0773; 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 :**  Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6509; fax: 425–917–6590; email: Rebel.Nichols@ 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– 2014–0773; Directorate Identifier 2014– NM–068–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 on Model 787 airplanes of a potential latent failure of the valve actuator circuitry, which was not identified during actuator development. The fuel shutoff valve actuator circuit design providescommon input power through microswitches to both the motor and position indications. The latent failure conditionhas the potential for a stuck microswitch, which could lead to a disagreement between the valve command and position indication. If a command is sent to change the valveposition and one of the internal microswitches is stuck in the depressed state, power would immediately provide indication that the valve transitioned to its commanded state, when the motor actually never received power to rotate. This condition, if not corrected, could result in the inability to shut off fuel to the engine or APU in the case of an engine or APU fire. If the fuel cannot be shut off to a fire, the engine or APU fire could be uncontrollable, which could lead to structural failure. Relevant Service Information We reviewed Boeing Service Bulletin B787–81205–SB280015–00, Issue 002, dated June 19, 2014. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for Docket No. FAA–2014–0773.

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 airplanes with certain part number shutoff valves to revise the maintenance or inspection program to add airworthiness limitation number 28– AWL–ACT, ‘‘Engine and APU Shut-Off Valve Actuator Test.’’ This proposed AD would also require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Difference Between this Proposed AD and the Service Information.’’

This proposed AD would require revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, an operator might not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval of an alternative method of compliance (AMOC) in accordance with the provisions of paragraph (k) of this proposed AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Explanation of ‘‘RC’’ Steps in Service Information

The FAA worked in conjunction with industry, under the Airworthiness Directives Implementation Aviation Rulemaking Committee, to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner’s/ operator’s understanding of crucial AD


### 68386 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules

requirements and help provide consistent judgment in AD compliance. The actions specified in the service information described previously include steps that are labeled as RC (required for compliance) because these steps have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition.

As noted in the specified service information, steps labeled as RC and all subordinate steps must be done to comply with the proposed AD. However, steps that are not labeled as RC are recommended. Those steps that are not labeled as RC may be deviated from, done as part of other actions, or done using accepted methods different from those identified in the service information without obtaining approval of an AMOC, provided the steps labeled as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps labeled as RC will require approval of an alternative method of compliance. Differences Between This Proposed AD and the Service Information

Although Boeing Service Bulletin B787–81205–SB280015–00, Issue 002, dated June 19, 2014, describes installing engine fuel shutoff valve and APU fuel shutoff valve actuators having part number (P/N) 53–0037, this proposed AD would prohibit installing valves having P/N 53–0037, and require installing certain other valves. We have coordinated this difference with Boeing.

The applicability of this proposed AD includes all Model 787–8 airplanes, which differs from the effectivity of the service information referenced previously. The parts are rotable, therefore, this proposed AD includes all Model 787–8 airplanes.
Costs of Compliance

We estimate that this proposed AD affects 6 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

Maintenance program revision ....................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $510 Engine and APU fuel shutoff valve actuator

replacement. 10 work-hours × $85 per hour = $850 ........... 0 850 5,100

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. Amend § 39.13 by adding the following new airworthiness directive (AD):
The Boeing Company: Docket No. FAA– 2014–0773; Directorate Identifier 2014– NM–068–AD.
(a) Comments Due Date

We must receive comments by January 2,
2015.
(b) Affected ADs

None.
(c) Applicability

This AD applies to all The Boeing Company Model 787–8 airplanes, certificated in any category.
(d) Subject

Air Transport Association (ATA) of America Code 28, Fuel.

(e) Unsafe Condition

This AD was prompted by a report of an error in the valve actuator design. We are issuing this AD to prevent latent failures of the fuel shutoff valve actuators, which could result in the inability to shut off fuel to the engine or APU in the case of an engine or APU fire. If the fuel cannot be shut off to a fire the engine or APU fire could be uncontrollable which could lead to structural failure.
(f) Compliance

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

Within 30 days after the effective date of this AD, revise the maintenance or inspection


### 68387 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules

program, as applicable, to add airworthiness limitation number 28–AWL–ACT, by incorporating the information specified in figure 1 to paragraph (g) of this AD into the Airworthiness Limitations Section of the Instructions for Continued Airworthiness. This may be accomplished by inserting a copy of airworthiness limitation number 28– AWL–ACT into the maintenance or inspection program, as applicable. For the airplanes identified in the applicability note of airworthiness limitation number 28–AWL– ACT, the initial compliance time for accomplishing the actions specified in figure 1 to paragraph (g) of this AD is within 10 days after accomplishment of the maintenance or inspection program revision required by this paragraph. When the engine and APU fuel shutoff valve actuators have been replaced as required by paragraph (i) of this AD, the airworthiness limitation number 28–AWL–ACT required by this paragraph may be removed from the maintenance or inspection program, as applicable.



### F IGURE 

### 1 TO 

### PARAGRAPH 

### (g) OF 

### THIS 

### AD: E NGINE AND 

### APU S HUT

### -O FF 

### VALVE 

### ACTUATOR 

### T EST

AWL No. Task Interval Applicability Description

28–AWL–ACT ......... ALI ........................... 10 Days NOTE ........ ALL NOTE ............... Engine and APU Shut-Off Valve Actuator Test. Concern: The fuel shutoff valve actuator design can

result in airplanes operating with a failed fuel shutoff actuator that is not reported. A latently failed fuel shutoff actuator would prevent fuelshut off to an engine. In the event of certain engine fires, the potential exists for an engine fire to be uncontrollable.Perform the following tests in accordance with Boeing Service Bulletin B787–81205–SB280015–00, Issue 002, dated June 19, 2014. 1. Do PART 1: ENGINE FUEL SHUTOFF VALVE

ACTUATOR TEST as described in Boeing Service Bulletin B787–81205–SB280015–00, Issue 002, dated June 19, 2014. a. If the left engine fuel shutoff valve actuator has

Part Number 53–0037, perform the left engine fuel shutoff valve actuator test. b. If the right engine fuel shutoff valve actuator

has Part Number 53–0037, perform the right engine fuel shutoff valve actuator test. c. If either test fails, repair faults as required

(refer to Boeing Airplane Maintenance Manual 28–22–02).2. Do PART 2: APU FUEL SHUTOFF VALVE ACTUATOR TEST as described in Boeing Service Bulletin B787–81205–SB280015–00, Issue 002, dated June 19, 2014. a. If the APU fuel shutoff valve actuator has part

number 53–0037, perform the APU fuel shutoff valve actuator test. b. If the test fails, before further flight requiring

APU availability, repair If the test fails, before further flight requiring APU availability, repair faults as required (refer to Boeing Airplane Maintenance Manual 28–25–03). NOTE: Dispatch may be permitted per MMEL 28–

25–03 if APU is not required for flight. INTERVAL NOTE: Not required on days when the

airplane is not used in revenue service. Must be done before further flight if it has been 10 or more calendar days since last inspectionAPPLICABILITY NOTE: This AWL applies to airplanes with Eaton Aerospace Ltd fuel shutoffvalve actuators having Part Number 53–0037 installed at the engine or APU spar shutoff location.

(h) No Alternative Actions and Intervals

Except as specified in paragraph (i) of this AD: After accomplishment of the maintenance or inspection program revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k) of this AD. (i) Replacement

Within 36 months after the effective date of this AD, replace the engine and APU fuel shutoff valve actuators having part number (P/N) 53–0037 with P/N 53–0049, in accordance with Part 5 or Part 6 of the Accomplishment Instructions of Boeing Service Bulletin B787–81205–SB280015–00, Issue 002, dated June 19, 2014, as applicable. When all the engine and APU fuel shutoff valve actuators have been replaced as required by this paragraph, the airworthiness limitation number 28–AWL–ACT required by paragraph (g) of this AD may be removed from the maintenance or inspection program, as applicable.
(j) Parts Installation Prohibition

As of the effective date of this AD, no person may install a motor operated valve actuator having P/N 53–0037 on any airplane in the following locations: Engine fuel shutoff valve, APU fuel shutoff valve, crossfeed valve, and defuel/isolation valve.


### 68388 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules

(k) 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 (l)(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) If the service information contains steps that are labeled as RC (Required for Compliance), those steps and all subordinate steps must be done to comply with this AD; any steps that are not labeled as RC are recommended. Those steps that are not labeled as RC may be deviated from, done as part of other actions, or done using accepted methods different from those identified in the specified service information without obtaining approval of an AMOC, provided the steps labeled as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps labeled as RC require approval of an
AMOC.

(l) Related Information

(1) For more information about this AD, contact Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6509; fax: 425–917–6590; email: Rebel.Nichols@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 November 5, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–27069 Filed 11–14–14; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0774; Directorate Identifier 2013–NM–154–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 supersede Airworthiness Directive (AD) 2006–22– 15, which applies to all Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747– 300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. AD 2006–22–15 currently requires repetitive inspections for cracking of certain panel webs and stiffeners of the nose wheel well (NWW), and corrective actions if necessary. AD 2006–22–15 also requires replacing certain panels with new panels, which terminates the repetitive inspections. Since we issued AD 2006–22–15, we received reports of fatigue cracking in the panel webs and stiffeners of the NWW prior to the inspection threshold of AD 2006–22–15. This proposed AD would reduce a compliance time and add certain inspections and repair if necessary. We are proposing this AD to prevent fatigue cracking of the NWW side and top panels, which could result in a NWW depressurization event severe enough to reduce the structural integrity of the fuselage.

**DATES :**  We must receive comments on this proposed AD by January 2, 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 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. 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– 0774; 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 (ACO), 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 proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2014–0774; Directorate Identifier 2013–NM–154–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

On October 25, 2006, we issued AD 2006–22–15, Amendment 39–14812 (71 FR 64884, November 6, 2006), for all Boeing Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747– 200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series