### 41891 Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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):
2012–14–08 Sikorsky Aircraft Corporation: Amendment 39–17122; Docket No. FAA–2012–0715; Directorate Identifier 2012–SW–039–AD.
(a) Applicability

This AD applies to Model S–92A helicopters, serial numbers 920006 through 920155, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as a crack in the main gearbox (MGB) housing cored oil passage. This condition could result in loss of oil, failure of the MGB, and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective August 1, 2012.
(d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions

Within 10 hours time-in-service (TIS) or 15 days, whichever occurs earlier, and thereafter before the first flight of each day, not to exceed 10 hours TIS between inspections, accomplish the following:

(1) Clean and inspect, using a 10x or higher power magnifying glass, the MGB housing for a crack in the inspection area shown in Figure 1 of Sikorsky S–92 Alert Service Bulletin No. ASB 92–63–032 Basic Issue, dated December 22, 2011.

Note to paragraph (e)(1) of this AD: A crack may be indicated by the presence of oil in the inspection area of the MGB housing.

(2) If there is a crack, before further flight, replace the MGB with an airworthy MGB.

(3) Compliance with the one-time eddycurrent inspection of the main module assembly of the MGB in accordance with the Accomplishment Instructions, paragraph 3.C, of Sikorsky S–92 ASB No. ASB 92–63–034 Basic Issue, dated March 8, 2012, by a technician certified to non-destructive testing Level II or greater is an optional terminating action for the inspection requirements of this AD. (f) Special Flight Permits

Special flight permits will not be issued. (g) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Schwetz, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; telephone (718) 238–7761; email michael.schwetz@faa.gov

.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
(h) Subject

Joint Aircraft Service Component (JASC) Code: 6320: Main Rotor Gearbox.
(i) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Sikorsky S–92 Alert Service Bulletin No. ASB 92–63–032 Basic Issue, dated December
22, 2011;

(ii) Sikorsky S–92 Alert Service Bulletin No. ASB 92–63–034 Basic Issue, dated March
8, 2012.

(3) For service information identified in this AD, contact Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT 06614; telephone (800) 562–4409; email address tsslibrary@sikorsky.com; or at http:// www.sikorsky.com

.

(4) You may review copies of this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.

(5) You may also review copies of this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go

to: http://www.archives.gov/federal

_register/ code

_ of

_ federal

_regulations/ ibr

_ locations.html

. Issued in Fort Worth, Texas, on July 2,

2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012–16944 Filed 7–16–12; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0677; Directorate Identifier 2012–NM–105–AD; Amendment**  **39–17114; AD 2012–13–12]**

**RIN 2120–AA64**

**Airworthiness Directives; Gulfstream Aerospace Corporation Airplanes** 

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

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model G–IV, GIV–X, GV, and GV–SP airplanes. This AD requires measuring to determine paint thickness on the flight control surfaces and corrective actions if necessary, and revising the Airplane Flight Manual (AFM). This AD was prompted by reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. We are issuing this AD to detect and correct paint thickness on flight controls, which could result in loss of control of the airplane due to flutter.

**DATES :**  This AD is effective August 1,
2012.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 1, 2012.

We must receive comments on this AD by August 31, 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: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this AD, contact Gulfstream Aerospace Corporation, Technical Publications


### 41892 Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations

Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@gulfstream.com; Internet http:// www.gulfstream.com/product

_ support/ technical

_

pubs/pubs/index.htm. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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 :**  Michael Cann, Senior Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park, GA 30337; phone 404–474–5548; fax 404–474–5605; email: michael.cann@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We received reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. Excessive paint thickness will affect the balance moment of the flight control surface. This condition, if not corrected, could result in loss of control of the airplane due to flutter.

Relevant Service Information

We reviewed the following service information, which describes procedures for measuring the paint thickness on both sides of each flight control surface (ailerons, rudder, and elevator) and corrective actions if necessary. The customer bulletins also describe procedures for revising the AFM to advise the flightcrew to not exceed a certain altitude until corrective actions have been accomplished. Corrective actions include removing the flight control surface and rebalancing, stripping, repainting with an average thickness less than 5.0 mils, and sanding/buffing down to 5.0 mils or less and re-measuring thicknesses (not recommended on surfaces with averages exceeding 7.0 mils).

• For Model G–IV airplanes: Gulfstream IV Customer Bulletin 223, including Part I and Part II Service Reply Cards, dated March 23, 2012, which includes Gulfstream GIV Airplane Flight Manual Supplement GIV–2012–01, dated March 13, 2012.

• For Model GV airplanes: Gulfstream V Customer Bulletin 196, including Part I and Part II Service Reply Cards, dated March 23, 2012, which includes Gulfstream GV Airplane Flight Manual Supplement GV–2012–01, dated March 13, 2012.

• For Model GIV–X airplanes: Gulfstream G450 Customer Bulletin 140, including Part I and Part II Service Reply Cards, dated March 23, 2012, which includes Gulfstream G450/G350 Airplane Flight Manual Supplement G450–2012–01, dated March 13, 2012.

• For Model GV–SP airplanes: Gulfstream G550 Customer Bulletin 121, including Part I and Part II Service Reply Cards, dated March 23, 2012, which includes Gulfstream G550 Airplane Flight Manual Supplement G550–2012–01, dated March 13, 2012; and Gulfstream G550 EASA Airplane Flight Manual Supplement EASA– G550–2012–01, dated March 14, 2012.

FAA’s Determination

We are issuing 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.
AD Requirements

This AD requires accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the AD and the Service Information.’’ This AD also requires sending the measurement and corrective action results to Gulfstream Aerospace Corporation.

Differences Between the AD and the Service Information

The customer bulletins specified in paragraph (g) of this AD incorporate the airplane flight manual supplement (AFMS) as an on-condition action. This AD requires operators to incorporate the AFMS within 20 days after the effective date of this AD. We have determined that this action is necessary to address the identified unsafe condition.

Although the customer bulletins specified in paragraph (g) of this AD specify that operators may contact the manufacturer for disposition of certain repair conditions, this AD requires operators to repair those conditions in accordance with a method approved by the FAA.
FAA’s Justification and Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule, because we received reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. Excessive paint thickness will affect the balance moment of the flight control surface. This condition, if not corrected, could result in loss of control of the airplane due to flutter. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include the docket number FAA–2012–0677 and Directorate Identifier 2012–NM–105–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD.
Costs of Compliance

We estimate that this AD affects 33 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:


### 41893 Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations

E STIMATED 

### C OSTS

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

Measurement ...................................................... 5 work-hours × $85 per hour = $425 ................. $0 $425 $14,025 Airplane flight manual revision ............................ 1 work-hour × $85 per hour = $85 ..................... 0 85 2,805

We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this AD.

According to the manufacturer, the costs of this 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

This AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD:

(1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866,

(2) Is not a ‘‘significant rule’’ under 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. Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): 2012–13–12 Gulfstream Aerospace Corporation: Amendment 39–17114; Docket No. FAA–2012–0677; Directorate Identifier 2012–NM–105–AD.
(a) Effective Date

This AD is effective August 1, 2012.
(b) Affected ADs

None. (c) Applicability

This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category.

(1) Gulfstream Aerospace Corporation Model G–IV airplanes, serial numbers 1265, 1286, 1298, 1301, 1347, 1372, 1378, 1380, 1423, 1458, and 1497.

(2) Gulfstream Aerospace Corporation Model GIV–X airplanes, serial numbers 4064, 4151, 4192, 4194, 4199, and 4214.

(3) Gulfstream Aerospace Corporation Model GV airplanes, serial numbers 612, 630, and 691.

(4) Gulfstream Aerospace Corporation Model GV–SP airplanes, serial numbers 5038, 5079, 5223, 5227, 5237, 5240, 5245, 5246, 5252, 5258, 5261, 5265, 5267, 5283, 5290, 5293, 5294, 5302, 5307, 5311, 5318, and 5320.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 27, Flight controls.
(e) Unsafe Condition

This AD was prompted by reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. We are issuing this AD to detect and correct paint thickness on flight controls, which could result in loss of control of the airplane due to flutter.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Airplane Flight Manual Revision

Within 20 days after the effective date of this AD, revise the airplane flight manual (AFM) by incorporating the applicable airplane flight manual supplement (AFMS) specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD. After accomplishing the actions in paragraph (h) of this AD, and all applicable corrective actions required by paragraph (i) of this AD, the AFMS specified in paragraph (g) of this AD may be removed from the AFM.

(1) For Model G–IV airplanes: Gulfstream IV Customer Bulletin 223, including Part I and Part II Service Reply Cards, dated March 23, 2012, which includes Gulfstream GIV Airplane Flight Manual Supplement GIV– 2012–01, dated March 13, 2012.

(2) For Model GV airplanes: Gulfstream V Customer Bulletin 196, including Part I and Part II Service Reply Cards, dated March 23, 2012, which includes Gulfstream GV Airplane Flight Manual Supplement GV– 2012–01, dated March 13, 2012.

(3) For Model GIV–X airplanes: Gulfstream G450 Customer Bulletin 140, including Part I and Part II Service Reply Cards, dated March 23, 2012, which includes Gulfstream G450/G350 Airplane Flight Manual Supplement G450–2012–01, dated March 13,
2012.

(4) For Model GV–SP airplanes: Gulfstream G550 Customer Bulletin 121, including Part I and Part II Service Reply Cards, dated March 23, 2012, which includes Gulfstream G550 Airplane Flight Manual Supplement G550–2012–01, dated March 13, 2012; and Gulfstream G550 EASA Airplane Flight Manual Supplement EASA–G550–2012–01, dated March 14, 2012.
(h) Measurement

At the applicable compliance time specified in paragraph (h)(1) or (h)(2) of this AD, measure the paint thickness on both sides of the flight control surfaces, in accordance with the Accomplishment Instructions of the applicable customer bulletin identified in paragraph (g) of this AD. If average paint thickness is equal to or less than 5.0 mils; or if average paint thickness is greater than 5.0 mils, but equal to or less than the serial number specific allowances provided in table 4 of the


### 41894 Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations

applicable customer bulletin identified in paragraph (g) of this AD: The AFMS specified in paragraph (g) of this AD may be removed from the AFM.

(1) For Model GIV–X, GV, and GV–SP airplanes: Within 90 days after the effective date of this AD.

(2) For Model G–IV airplanes: Within 180 days after the effective date of this AD.
(i) Corrective Actions

(1) If, during the measurement required by paragraph (h) of this AD, the average paint thickness is greater than the serial number specific allowances provided in table 4 of the applicable customer bulletin specified in paragraph (g) of this AD, and is equal to or greater than 13.0 mils: Before further flight, repair, in accordance with a method approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD.

(2) If, during the measurement required by paragraph (h) of this AD, the average paint thickness is greater than the serial number specific allowances provided in table 4 of the applicable customer bulletin specified in paragraph (g) of this AD, but is less than 13 mils: Within 12 months after the effective date of this AD, do all applicable corrective actions, in accordance with the applicable customer bulletin specified in paragraph (g) of this AD, except as required by paragraph (j) of this AD. After accomplishing the applicable corrective actions, the AFMS specified in paragraph (g) of this AD may be removed from the AFM.
(j) Exception

Where the customer bulletins identified in paragraph (g) of this AD specify to contact Gulfstream Aerospace Corporation for corrective actions, this AD requires doing corrective actions before further flight, in accordance with a method approved by the Manager, Atlanta ACO. For a repair method to be approved by the Manager, Atlanta ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. (k) Reporting

(1) Submit a report of the measurements required by paragraph (h) of this AD, including the dimensions obtained from tables 1, 2, and 3, of the applicable customer bulletin specified in paragraph (g) of this AD. Submit the report using the Part I Service Reply Card in the applicable customer bulletin identified in paragraph (g) of this AD, to Gulfstream Aerospace Corporation, at the applicable time specified in paragraph (k)(1)(i) or (k)(1)(ii) of this AD. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120 0056.

(i) If the measurement was done on or after the effective date of this AD: Submit the report within 30 days after the measurement.

(ii) If the measurement was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.

(2) Submit a report of compliance with the corrective actions required by paragraph (i) of this AD, using the Part II Service Reply Card in the applicable customer bulletin identified in paragraph (g) of this AD, to Gulfstream Aerospace Corporation, at the applicable time specified in paragraph (k)(2)(i) or (k)(2)(ii) of this AD.

(i) If the corrective action was done on or after the effective date of this AD: Submit the report within 30 days after accomplishing the corrective action.

(ii) If the corrective action was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
(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), may be issued to operate the airplane to a location where the requirements of this AD can be accomplished if the applicable AFM specified in paragraph (g) of this AD has been revised as required by paragraph (g) of this AD.
(m) Paperwork Reduction Act Burden Statement

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200.
(n) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Atlanta 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.
(o) Related Information

For more information about this AD, contact Michael Cann, Senior Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, GA 30337; phone 404–474– 5548; fax 404–474–5605; email: michael.cann@faa.gov.
(p) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise.

(i) Gulfstream IV Customer Bulletin 223, dated March 23, 2012, which includes the following attachments:

(A) Part I Service Reply Card, dated March 23, 2012.

(B) Part II Service Reply Card, dated March 23, 2012.

(C) Gulfstream GIV Airplane Flight Manual Supplement GIV–2012–01, dated March 13,
2012.

(ii) Gulfstream V Customer Bulletin 196, dated March 23, 2012, which includes the following attachments:

(A) Part I Service Reply Card, dated March 23, 2012.

(B) Part II Service Reply Card, dated March 23, 2012.

(C) Gulfstream GV Airplane Flight Manual Supplement GV–2012–01, dated March 13,
2012.

(iii) Gulfstream G450 Customer Bulletin 140, dated March 23, 2012, which includes the following attachments:

(A) Part I Service Reply Card, dated March 23, 2012.

(B) Part II Service Reply Card, dated March 23, 2012.

(C) Gulfstream G450/G350 Airplane Flight Manual Supplement G450–2012–01, dated March 13, 2012.

(iv) Gulfstream G550 Customer Bulletin 121, dated March 23, 2012, which includes the following attachments:

(A) Part I Service Reply Card, dated March 23, 2012.

(B) Part II Service Reply Card, dated March 23, 2012.

(C) Gulfstream G550 Airplane Flight Manual Supplement G550–2012–01, dated March 13, 2012.

(D) Gulfstream G550 EASA Airplane Flight Manual Supplement EASA–G550–2012–01, dated March 14, 2012.

(3) For service information identified in this AD, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, GA 31402–2206; telephone 800–810–4853; fax 912–965–3520; email pubs@gulfstream.com; Internet http:// www.gulfstream.com/product

_ support/ technical

_ pubs/pubs/index.htm. (4) You may review copies of the service information at the FAA, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call
425–227–1221.

(5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go
to: http://www.archives.gov/federal-register/ cfr/ibr

_ locations.html.


### 41895 Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations

Issued in Renton, Washington, on June 28,
2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–16637 Filed 7–16–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0147; Directorate Identifier 2011–NM–067–AD; Amendment**  **39–17116; AD 2012–14–02]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 767–200 and –300 series airplanes. That AD currently requires replacement of the existing deactivation pin, aft cascade pin bushing, and pin insert on each thrust reverser half with new, improved components. This new AD requires a dye penetrant inspection for cracking of the rivet holes of the bushing plate and repair or replacement, if necessary; and for certain airplanes, replacing the existing bushing with a new bushing and deactivation pin, and installing a new or serviceable stowage bracket for the deactivation pins on all airplanes powered by Pratt & Whitney JT9D series engines. This AD was prompted by reports that certain airplanes require installation of a new bushing and deactivation pin with increased load carrying capability and all airplanes powered by Pratt & Whitney JT9D series engines require installation of a new bracket for stowing the deactivation pin. We are issuing this AD to prevent failure of the thrust reverser deactivation pins, which could fail to prevent a deployment of a deactivated thrust reverser in flight and consequent reduced controllability of the airplane.

**DATES :**  This AD is effective August 21,
2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 21, 2012.

The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of November 5, 2002 (67 FR 61478, October 1, 2002). **ADDRESSES :**  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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Rebel Nichols, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6509; fax: 425–917–6590; email: rebel.nichols@faa.gov

.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a Notice of Proposed Rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2002–19–11, Amendment 39–12891 (67 FR 61478, October 1, 2002). That AD applies to the specified products. The NPRM published in the Federal Register on February 22, 2012 (77 FR 10406). That NPRM proposed to continue to require replacement of the existing deactivation pin, aft cascade pin bushing, and pin insert on each thrust reverser half with new, improved components. That NPRM also proposed to require a dye penetrant inspection for cracking of the rivet holes of the bushing plate and repair or replacement, if necessary; and for certain airplanes, replacing the existing bushing with a new bushing and deactivation pin, and installing a new or serviceable stowage bracket for the deactivation pins on all airplanes powered by Pratt & Whitney JT9D series engines.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (77 FR 10406, February 22, 2012) and the FAA’s response to each comment. Support for Proposed Rule (77 FR 10406, February 22, 2012)

Boeing concurs with the content of the proposed rule (77 FR 10406, February 22, 2012). Request To Provide Credit for Previous Actions

Atlas Air requested that we revise the NPRM (77 FR 10406, February 22, 2012) to provide credit for actions required by paragraph (h)(2) of the NPRM, if those actions were accomplished before the effective date of the AD using Boeing Service Bulletin 767–78A0089, Revision 3, dated December 18, 2003.

We agree. Paragraph (i) of the NPRM (77 FR 10406, February 22, 2012) provided credit for actions required by paragraph (g) of the NPRM if those actions were performed before the effective date of the NPRM using Boeing Service Bulletin 767–78A0089, Revision 2, dated March 13, 2003; Boeing Service Bulletin 767–78A0089, Revision 3, dated December 18, 2003; or Boeing Service Bulletin 767–78A0089, Revision 4, dated March 6, 2008. We have revised paragraph (i) of this final rule to also provide credit for actions required by paragraph (h)(2) of this AD, if those actions were performed before the effective date of this AD. Explanation of Changes Made to This AD

We have revised certain headings throughout this AD and revised Note 1 of the NPRM (77 FR 10406, February 22, 2012) to paragraph (g)(2) of this AD. We have also revised paragraph (i) of this AD. These changes have not affected the intent of those paragraphs. Explanation of Updated Credit Language

We have revised the heading and wording for paragraph (i) of this AD to provide appropriate credit for previous accomplishment of certain actions. This change does not affect the intent of that paragraph.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD