### 2666 Federal Register / Vol. 77, No. 12 / Thursday, January 19, 2012 / Proposed Rules

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– 2011–1415; Directorate Identifier 2011– NM–145–AD.
(a) Comments Due Date

We must receive comments by March 5,
2012.
(b) Affected ADs

None. (c) Applicability

This AD applies to all The Boeing Company Model 717–200 airplanes, certificated in any category.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 5510, Horizontal Stabilizer Structure.
(e) Unsafe Condition

This AD was prompted by reports of cracks found on the center section ribs of the horizontal stabilizers. We are issuing this AD to detect and correct cracks in the left and right bearing lugs of the rib hinge spreading at the same time, which could result in failure of both hinge bearing lugs. Failure of the hinge bearing lugs could result in the inability of the horizontal stabilizer to sustain flight loads and therefore reduce the controllability of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Repetitive Eddy Current High Frequency (ETHF) Inspections

Before the accumulation of 35,000 total flight cycles, or within 8,275 flight cycles after the effective date of this AD, whichever occurs later: Do an ETHF inspection for cracks of the aft face on the left and right rib hinge bearing lugs of the center section of the horizontal stabilizer, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011. If no crack is found, repeat the inspection thereafter at intervals not to exceed 10,500 flight cycles.

(h) Crack Measurement

If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, measure the length of the crack, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011. (i) Blend Out Repair, ETHF Inspections, and Corrective Action for Certain Crack Lengths

For any crack that meets ‘‘Condition 2A’’ of Table 1 of 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011: Do the actions in paragraphs (i)(1) and (i)(2) of this AD.

(1) Before further flight, do a blend out repair, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011.

(2) Within 14,200 flight cycles after accomplishing the blend out repair required by paragraph (i)(1) of this AD: Do an ETHF inspection of the blend out repair area for cracking, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 5,400 flight cycles.

(i) If any crack is found during the ETHF inspection required by paragraph (i)(2) of this AD: Before further flight, remove the cracked center section rib of the horizontal stabilizer and install a new center section rib, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011.

(ii) Within 35,000 flight cycles after the installation of the new center section rib, do the actions in paragraph (g) of this AD.
(j) Corrective Action for Certain Crack Lengths

For any crack that meets ‘‘Condition 2D’’ of Table 1 of 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011: Before further flight, remove the cracked center section rib of the horizontal stabilizer and install a new center section rib, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011. Within 35,000 flight cycles after the installation of the new rib, do the actions in paragraph (g) of this AD.
(k) No Reporting Requirement

Although Boeing Alert Service Bulletin 717–55A0011, dated May 17, 2011, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (l) Alternative Methods of Compliance (AMOCs)

(1) The Manager Los Angeles 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.

(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, Los Angeles 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.

(m) Related Information

(1) For more information about this AD, contact George Garrido, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: (562) 627– 5357; fax: (562) 627–5210; email: George.Garrido@faa.gov.

(2) For service information identified in this AD, Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; phone: (206) 544–5000, extension 2; fax: (206) 766–5683; email: dse.boecom@boeing.com; 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 January 6, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–858 Filed 1–18–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–1417; Directorate Identifier 2011–NM–159–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 777 airplanes. This proposed AD was prompted by reports that escape slides/ rafts did not deploy due to galvanic corrosion of the door-mounted slide/raft packboard release mechanisms. This proposed AD would require doing a general visual inspection of the housing


### 2667 Federal Register / Vol. 77, No. 12 / Thursday, January 19, 2012 / Proposed Rules

assembly of the packboard release mechanism to determine if its surface treatment has been sealed, and if unsealed, replacing the housing assembly with a new or serviceable housing assembly. We are proposing this AD to detect and correct corrosion of the packboard release mechanisms, which could interfere with escape slide/ raft deployment, prohibit doors from opening in the armed mode, and cause consequent delay and injury during evacuation of passengers and crew from the cabin in the event of an emergency.

**DATES :**  We must receive comments on this proposed AD by March 5, 2012.

**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, Washington 98124–2207; telephone (206) 544–5000, extension 1; fax (206) 766–5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. For Air Cruisers service information identified in this AD, contact Air Cruisers Company, 1747 State Route 34, Wall, New Jersey 07727–3935; telephone: (732) 681–3527; fax: (732) 681–9163; email: Aircruisers@zodiacaerospace.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 :**  Ana Martinez Hueto, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917– 6592; fax: (425) 917–6591; email: ana.m.hueto@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– 2011–1417; Directorate Identifier 2011– NM–159–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 that escape slides/rafts did not deploy due to galvanic corrosion of door-mounted slide/raft packboard release mechanisms. Such corrosion, if not detected and corrected, could interfere with escape slide/raft deployment, prohibit doors from opening in the armed mode, and cause consequent delay and injury during evacuation of passengers and crew from the cabin in the event of an emergency.

Relevant Service Information

We reviewed Boeing Special Attention Service Bulletin 777–25– 0507, dated June 30, 2011. The service information describes procedures for doing a general visual inspection of the housing assembly of the door-mounted slide/raft packboard release mechanism to determine if its surface treatment has been sealed, and if unsealed, replacing the housing assembly with a new or serviceable housing assembly.

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. Costs of Compliance

We estimate that this proposed AD affects 161 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 ........................ Between 4 and 16 work-hours × $85 per hour = Between $340 and $1,360. $0 Between $340 and $1,360. Between $54,740 and $218,960.

We estimate the following costs to do any necessary replacements 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 replacements:


### 2668 Federal Register / Vol. 77, No. 12 / Thursday, January 19, 2012 / Proposed Rules

O N 

### -CONDITION 

### COSTS

Action Labor cost Parts cost Cost per product

Replacement .................................... 1 work-hour × $85 per hour = $85 ............................................................ $137 $222

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– 2011–1417; Directorate Identifier 2011– NM–159–AD.
(a) Comments Due Date

We must receive comments by March 5,
2012.
(b) Affected ADs

None. (c) Applicability

This AD applies to The Boeing Company Model 777–200, –200LR, –300, –300ER, and 777F series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 777–25–0507, dated June 30, 2011.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 25, Equipment/Furnishings.
(e) Unsafe Condition

This AD was prompted by reports that escape slides/rafts did not deploy due to galvanic corrosion of the door-mounted slide/raft packboard release mechanisms. We are issuing this AD to detect and correct corrosion in the packboard release mechanisms, which could interfere with escape slide/raft deployment, prohibit doors from opening in the armed mode, and cause consequent delay and injury during evacuation of passengers and crew from the cabin in the event of an emergency.
(f) Compliance

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

Within 42 months after the effective date of this AD, at the applicable passenger/crew entry doors identified in Boeing Special Attention Service Bulletin 777–25–0507, dated June 30, 2011: Do a general visual inspection of the housing assembly of the packboard release mechanism to determine if its surface treatment has been sealed; and if unsealed, before further flight, replace the housing assembly with a new or serviceable housing assembly, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–25– 0507, dated June 30, 2011.

Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’

Note 2: Boeing Special Attention Service Bulletin 777–25–0507, dated June 30, 2011, refers to Air Cruisers Service Bulletin 777 107–25–30, dated September 30, 2010, as an additional source of guidance for inspecting and installing new housing assembly of the door-mounted slide/raft packboard release mechanism.

(h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: -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.
(i) Related Information

(1) For more information about this AD, contact Ana Martinez Hueto, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: (425) 917–6592; fax: (425) 917–6591; email: ana.m.hueto@faa.gov.

(2) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone (206) 544–5000, extension 1; fax (206) 766–5680; email


### 2669 Federal Register / Vol. 77, No. 12 / Thursday, January 19, 2012 / Proposed Rules

me.boecom@boeing.com; Internet https:// www.myboeingfleet.com. For Air Cruisers service information identified in this AD, contact Air Cruisers Company, 1747 State Route 34, Wall, New Jersey 07727–3935; telephone: (732) 681–3527; fax: (732) 681– 9163; email: Aircruisers@zodiacaerospace.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 January 6, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–856 Filed 1–18–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–1419; Directorate Identifier 2010–NM–281–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 an existing airworthiness directive (AD) that applies to certain The Boeing Company Model 737–300, –400, and –500 series airplanes. The existing AD currently requires repetitive inspections for cracking of the crown area of the fuselage skin, and corrective actions if necessary. Since we issued that AD, we received additional reports of cracking at the horizontal chem-mill steps away from the lap joints over the entire crown area, and vertical chem-mill cracks adjacent to the butt joints. This proposed AD would add repetitive inspections for cracking using different inspection methods and would inspect additional areas, and corrective actions if necessary. This proposed AD would also require additional repairs to previously repaired areas and repetitive inspections for loose fasteners and replacement if necessary in certain previously repaired areas. This proposed AD would also reduce certain compliance times and extend certain other compliance times. We are proposing this AD to detect and correct fatigue cracking of the fuselage skin, which could cause the fuselage skin to fracture and fail, and result in rapid decompression of the airplane.

**DATES :**  We must receive comments on this proposed AD by March 5, 2012.

**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 AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone (206) 544–5000, extension 1; fax (206) 766–5680; email me.boecom@boeing.com; 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 :**  Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6447; fax: (425) 917–6590; email: wayne.lockett@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–2011–1419; Directorate Identifier 2010–NM–281–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 June 15, 2005, we issued AD 2005–13–27, amendment 39–14164 (70 FR 36821, June 27, 2005), for certain Boeing Model 737–300, –400, and –500 series airplanes. That AD requires repetitive inspections for cracking of the crown area of the fuselage skin, and corrective actions if necessary. That AD resulted from a Model 737 fuselage structure test and fatigue analysis that indicate fuselage skin cracking could occur between 21,000 and 42,000 total flight cycles. We issued that AD to detect and correct fatigue cracking of the fuselage skin, which could cause the fuselage skin to fracture and fail, and result in rapid decompression of the airplane. Actions Since Existing AD Was Issued

Since we issued AD 2005–13–27, amendment 39–14164 (70 FR 36821, June 27, 2005), additional reports of cracking at the horizontal chem-mill steps away from the lap joints over theentire crown area, and vertical chemmill cracks adjacent to the butt joints, have been received. Although there were no changes to the applicability in AD 2005–13–17, we have changed paragraph (c) of the proposed AD to refer to Boeing Alert Service Bulletin 737–53A1234, Revision 2, dated November 24, 2010.

Relevant Service Information

We reviewed Boeing Alert Service Bulletin 737–53A1234, Revision 2, dated November 24, 2010. Boeing Special Attention Service Bulletin 737– 53–1234, Revision 1, dated March 31, 2005, was referred to for accomplishing the actions in AD 2005–13–27, amendment 39–14164 (70 FR 36821, June 27, 2005). Boeing Alert Service Bulletin 737–53A1234, Revision 2, dated November 24, 2010, describesprocedures for repetitive nondestructive inspections (NDI) (medium