## 73460 Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules

Alert Service Bulletin 747–53A2088, Revision 4, dated January 11, 2013, until accomplishment of the requirements of paragraph (h) of this AD.
(h) Modification

For airplanes that have not been modified as specified in Boeing Service Bulletin 747– 53–2088: At the applicable time specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2088, Revision 4, dated January 11, 2013, except as required by paragraph (j)(1) of this AD, modify the tension ties, including doing an open-hole high frequency eddy current inspection for cracks, as applicable, and all applicable corrective actions, in accordance with Part III of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2088, Revision 4, dated January 11, 2013, except as required by paragraph (j)(2) of this AD. All applicable corrective actions must be done before further flight. This modification terminates the repetitive inspection requirements of paragraph (g) of this AD.
(i) Post-Modification Repetitive Inspections

For airplanes that have been modified as specified in Boeing Service Bulletin 747–53– 2088: At the applicable time in Table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2088, Revision 4, dated January 11, 2013, do a detailed inspection for cracking of the tension tie at BS 760 or 780, and do all applicable corrective actions, in accordance with Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2088, Revision 4, dated January 11, 2013, except as required by paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable time in Table 2 specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2088, Revision 4, dated January 11, 2013. Boeing Alert Service Bulletin 747–53A2088, Revision 4, datedJanuary 11, 2013, notes that additional postmodification inspections are specified in Boeing Service Bulletin 747–53A2502; those post-modification inspections are required by AD 2006–01–07, Amendment 39–14446 (71 FR 1947, January 12, 2006).
(j) Exceptions to Service Information Specifications

(1) Where Boeing Alert Service Bulletin 747–53A2088, Revision 4, dated January 11, 2013, specifies a compliance time ‘‘after the Revision 4 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD.

(2) Where Boeing Alert Service Bulletin 747–53A2088, Revision 4, dated January 11, 2013, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(k) Credit for Previous Actions

This paragraph provides credit for the actions specified in this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2088, Revision 3, dated September 8, 1994. (l) Special Flight Permit

Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed.
(m) 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 (n)(2) 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 84–19–01, Amendment 39–4913 (49 FR 35365, September 17, 1984), are approved as AMOCs for the corresponding requirements of paragraph (g) (the retained detailed inspections) and paragraph (i) of this AD, but not as AMOCs for the high frequency eddy current inspections required by paragraph (g) of this AD.

(n) Related Information

(1) For more information about this AD, contact Roger Caldwell, Aerospace Engineer, Denver Aircraft Certification Office, FAA, 26805 East 68th Avenue, Denver, CO 80249; phone: 303–342–1086; fax: 303–342–1088; email: Roger.Caldwell@faa.gov.

(2) For information about AMOCs, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov.

(3) 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 29, 2013. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–29128 Filed 12–5–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0978; Directorate Identifier 2013–NM–120–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 767–400ER series airplanes. This proposed AD was prompted by reports of turbine wheel bursts in the air driven pump (ADP) turbine gearbox assembly (TGA), which resulted in the release of high energy fragments. This proposed AD would require replacing the existing ADP TGA with an improved ADP TGA. We are proposing this AD to prevent fragments from an uncontained turbine wheel burst penetrating the fuselage and striking passengers, or penetrating the wing-to-body fairing and striking ground handling or maintenance personnel, causing serious injury.

**DATES** 

### : We must receive comments on this proposed AD by January 21, 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 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;


## 73461 Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules

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, Washington. 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**

### : Kenneth Frey, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6468; fax: 425–917–6190; email: kenneth.frey@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– 2013–0978; Directorate Identifier 2013– NM–120–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 uncontained failures of the turbine wheel in the ADP TGA assembly. Flightcrews noticed a reduction in center hydraulic system pressure and upon landing, found damage to the ADP TGA assembly, the left, aft, wing-to-body fairing, and to the airplane skin. Boeing’s analysis determined that the existing ADP TGA assembly design cannot adequately contain fragments caused by a turbine wheel burst. Fragments from an uncontained turbine wheel burst could penetrate the fuselage and strikepassengers, or penetrate the wing-tobody fairing and strike ground handling or maintenance personnel, causing serious injury.

Relevant Service Information

We reviewed Boeing Special Attention Service Bulletin 767–29– 0113, dated May 29, 2013. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for Docket No. FAA–2013–0978.

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 identified previously. Costs of Compliance

We estimate that this proposed AD affects 37 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

Replacement ........................... 7 work-hours × $85 per hour = $595 ..................................... $114,705 $115,300 $4,266,100



### 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:


## 73462 Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules

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– 2013–0978; Directorate Identifier 2013–
NM–120–AD.
(a) Comments Due Date

We must receive comments by January 21,

2014.
(b) Affected ADs

None.
(c) Applicability

This AD applies to The Boeing Company Model 767–400ER series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 767–29–0113, dated May 29, 2013.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 29, Hydraulic Power.

(e) Unsafe Condition

This AD was prompted by reports of turbine wheel bursts in the air driven pump (ADP) turbine gearbox assembly (TGA), which resulted in the release of high energy fragments. We are issuing this AD to prevent fragments from an uncontained turbine wheel burst penetrating the fuselage andstriking passengers, or penetrating the wingto-body fairing and striking ground handling or maintenance personnel, causing serious injury.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Replacement of Turbine Gearbox Assembly

Except as required by paragraph (i) of this AD: At the time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 767–29–0113, dated May 29, 2013, replace the existing ADP TGA having part number N012000000 or N012000000–1 with an improved ADP TGA having part number N012000000–2 or N012000000–3, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767–29–0113, dated May 29,

2013.

Note 1 to paragraph (g) of this AD: Guidance on modifying an existing ADP TGA so it can be re-identified as part number N012000000–2 or N012000000–3 can be found in Fairchild Controls Service Bulletin N012000000–29–03, Revision 2, dated January 29, 2013.

(h) Parts Installation Prohibition

As of the effective date of this AD, no person may install an ADP TGA having part number N012000000 or N012000000–1 on any airplane. (i) Exception to Service Information Specifications

Where Boeing Special Attention Service Bulletin 767–29–0113, dated May 29, 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.
(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 paragraph (k) 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.

(k) Related Information

(1) For more information about this AD, contact Kenneth Frey, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6468; fax: 425–917– 6190; email: kenneth.frey@faa.gov.

(2) For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC2H–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, Washington. For information on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on November 26, 2013. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–29136 Filed 12–5–13; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–1024; Directorate Identifier 2013–NM–140–AD]** 

**RIN 2120–AA64**



### Airworthiness Directives; Bombardier, **Inc. 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 Bombardier, Inc. Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes. This proposed AD wasprompted by reports of a fractured wingto-fuselage strut attachment joint bolt. This proposed AD would require doing a torque check of all wing-to-fuselage strut attachment joint bolts, and repairing or replacing if necessary. For certain airplanes this proposed AD would require a detailed inspection for corrosion, damage, and wear of each wing-to-fuselage strut attachment joint bolt and associated hardware, and replacing if necessary; and a borescope inspection for corrosion and damage of the bore hole and barrel nut threads, and repairing or replacing if necessary. We are proposing this AD to detect and correct fractured bolts, which could result in reduced structural integrity of the wing-to-fuselage strut attachment joint and subsequent loss of the wing.

**DATES** 

### : We must receive comments on this proposed AD by January 21, 2014.

**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 Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email