## 42658 Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations

A71N001–12, Rev. 2, dated February 27,
2013.
(k) Parts Prohibition

As of the effective date of this AD, no person may install any aft engine mount retainer with a dull finish on any airplane. The instructions of Airbus AOT A71N001– 12, Rev. 2, dated February 27, 2013; or the Accomplishment Instructions of Goodrich Service Bulletin RA32071–146, Rev. 2, dated July 26, 2012; may be used to verify the correct finish of the part.
(l) Credit for Previous Actions

This paragraph provides credit for actions required by paragraphs (g), (i), and (j) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A71N001–12, Rev. 1, dated August 9, 2012, which is not incorporated by reference in this AD.
(m) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9 -ANM-116- AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD.

(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature.
(n) Special Flight Permits

Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified (if the operator elects to do so), provided no dull finish aft engine mount retainers that are cracked or have failed are installed.

(o) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013–0050, dated March 5, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!document Detail;D=FAA-2013-1028-0002

.

(2) Service information identified in this AD that is not incorporated by reference may be viewed at the addresses specified in paragraphs (p)(3), (p)(4), and (p)(5) of this
AD.
(p) 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 this AD specifies otherwise.

(i) Airbus Alert Operators Transmission A71N001–12, Rev. 2, dated February 27, 2013. The first page of this document contains the document number, revision, and date; no other page of this document contains this information.

(ii) Goodrich Service Bulletin RA32071– 146, Rev. 2, dated July 26, 2012.

(3) For Airbus service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com ; Internet http://www.airbus.com

.

(4) For Goodrich Corporation service information identified in this AD, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910–2098; phone: 619–691–2719; email: jan.lewis@ goodrich.com ; Internet: http:// www.goodrich.com/TechPubs

.

(5) You may view this 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.

(6) You may view 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/cfr/ibrlocations.html

.

Issued in Renton, Washington, on July 3,

2014. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–16536 Filed 7–22–14; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0292; Directorate Identifier 2014–CE–011–AD; Amendment**  **39–17904; AD 2014–15–02]**

**RIN 2120–AA64**



### Airworthiness Directives; GROB– **WERKE GMBH & CO KG Gliders**

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for GROB– WERKE GMBH & CO KG Models G102 STANDARD ASTIR III, G102 CLUB ASTIR III, and G102 CLUB ASTIR IIIb gliders and BURKHART GROB LUFT— UND RAUMFAHRT GmbH & CO KG Models G103 TWIN II, G103A TWIN II ACRO, G103C TWIN III ACRO, and G 103 C Twin III SL gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as plastic control cable pulleys developing cracks due to aging. We are issuing this AD to require actions to address the unsafe condition on these products.

**DATES** 

### : This AD is effective August 27,
2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 27, 2014.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0292; or in person at 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 service information identified in this AD, contact Fiberglas-Technik Rudolf Lindner GmbH & Co. KG, Steige 3, D–88487 Walpertshofen, Germany; telephone: +49 (0) 7353/22 43; fax: +49 (0) 7353/30 96; email: info@LTBLindner.com ; Web site: http://www.ltblindner.com/home.104.html. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.


## 42659 Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations

**FOR FURTHER INFORMATION CONTACT** 

### : Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329–4090; email: jim.rutherford@ faa.gov

. **SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to GROB–WERKE GMBH & CO KG Models G102 STANDARD ASTIR III, G102 CLUB ASTIR III, and G102 CLUB ASTIR IIIb gliders and BURKHART GROB LUFT—UND RAUMFAHRT GmbH & CO KG Models G103 TWIN II, G103A TWIN II ACRO, G103C TWIN III ACRO, and G 103 C Twin III SL gliders. The NPRM was published in the Federal Register on May 6, 2014 (79 FR 25753). The NPRM proposed to correct an unsafe condition for the specified products and was based on MCAI originated by an aviation authority of another country. The MCAI states:

Control cable pulleys made from plastic (white or brown material) in the rudder control unit were reported to develop cracks due to aging. In one case, jamming of the rudder control unit was reported.

This condition, if not detected and corrected, could cause cable pulleys to break, potentially jamming the rudder control unit and resulting in loss of control of the sailplane.

To address this potential unsafe condition, Fiberglas-Technik issued Technische Mitteilung/Service Bulletin TM–G05/SB–G05 and Anweisung/Instructions A/I–G05 (one document) to provide instructions for the replacement of plastic cable pulleys with pulleys made from aluminium.

For the reason described above, this AD requires identification and replacement of plastic cable pulleys in the rudder control unit.

Plastic cable pulleys may also be installed in the cable circuits of pedal adjustment and/ or tow hook actuation, their replacement is not required by this AD.


### The MCAI can be found in the AD docket on the Internet at: http://www. regulations.gov/#!documentDetail; D=FAA-2014-0292-0002

. Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 25753, May 6, 2014) or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (79 FR 25753, May 6, 2014) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 25753, May 6, 2014). Costs of Compliance

We estimate that this AD will affect 118 products of U.S. registry. We also estimate that it would take about .5 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour.

Based on these figures, we estimate the cost of the AD on U.S. operators to be $5,015, or $42.50 per product.

In addition, we estimate that any necessary follow-on actions would take about 2 work-hours and require parts costing $244, for a cost of $414 per product. We have no way of determining the number of products that may need these actions. 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 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 this AD:

(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. 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– 0292; 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 the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5527) is in the **ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt. 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 AD:

2014–15–02 GROB-WERKE GMBH & CO KG and BURKHART GROB LUFT-UND RAUMFAHRT GmbH & CO KG: Amendment 39–17904; Docket No. FAA–2014–0292; Directorate Identifier 2014–CE–011–AD.
(a) Effective Date

This airworthiness directive (AD) becomes effective August 27, 2014.

(b) Affected ADs

None. (c) Applicability

This AD applies to GROB-WERKE GMBH & CO KG Models G102 STANDARD ASTIR III, G102 CLUB ASTIR III, and G102 CLUB ASTIR IIIb gliders and BURKHART GROB LUFT-UND RAUMFAHRT GmbH & CO KG Models G103 TWIN II, G103A TWIN II


## 42660 Federal Register / Vol. 79, No. 141 / Wednesday, July 23, 2014 / Rules and Regulations

ACRO, G103C TWIN III ACRO and Model G 103 C Twin III SL gliders with the following serial numbers (S/N), certificated in any category.

(1) G102 STANDARD ASTIR III, S/N 5501 through 5652.

(2) G102 CLUB ASTIR III, S/N 5501 through 5652.

(3) G102 CLUB ASTIR IIIb, S/N 5501 through 5652.

(4) G103 TWIN II, S/N 3730 through 34078. (5) G103A TWIN II ACRO, S/N 3730 through 34078.

(6) G103C TWIN III ACRO, S/N 34101 through 34203.

(7) G 103 C Twin III SL, S/N 35002 through
35051. (d) Subject

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

(e) Reason

This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as plastic control cable pulleys developing cracks due to aging. We are issuing this AD to detect and correct plastic control cable pulleys in the rudder control unit, which could lead to breaking of the pulley and potentially jamming the rudder control unit, possibly resulting in loss of control of the glider.
(f) Actions and Compliance

Comply with this AD within the compliance times specified in paragraphs (f)(1) through (f)(3) of this AD, unless already done.

(1) For all Models G103C TWIN III ACRO and G 103 C Twin III SL gliders: Within 3 months after August 27, 2014 (the effective date of this AD), inspect the rudder control unit for installation of plastic cable pulleys. If plastic cable pulleys are installed, before further flight, replace the plastic cable pulleys with aluminum cable pulleys following the actions and instructions of Fiberglas-Technik Rudolf Lindner GmbH & Co. KG Service Bulletin SB–G05 and Fiberglas-Technik Rudolf Lindner GmbH & Co. KG Instructions A/I–G05, both dated January 17, 2014.

(2) For all Models G102 STANDARD ASTIR III, G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, G103 TWIN II, and G103A TWIN II ACRO gliders: Within 1 month after August 27, 2014 (the effective date of this AD), inspect the rudder control unit for installation of plastic cable pulleys. If plastic cable pulleys are installed, before further flight, replace the plastic cable pulleys with aluminum cable pulleys following the actions and instructions of Fiberglas-Technik Rudolf Lindner GmbH & Co. KG Service Bulletin SB–G05 and Fiberglas-Technik Rudolf Lindner GmbH & Co. KG Instructions A/I–G05, both dated January 17, 2014.

(3) As of August 27, 2014 (the effective date of this AD), do not install any plastic control cable pulley in the rudder control unit of any glider identified in paragraphs (c)(1) through (c)(7) of this AD. (g) Other FAA AD Provisions The following provisions also apply to this
AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329– 4090; email: jim.rutherford@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(h) Related Information

Refer to European Aviation Safety Agency (EASA) AD No.: 2014–0067, dated March 18, 2014, for related information. The MCAI can be found in the AD docket on the Internet at: http://www.regulations.gov/#!document Detail;D=FAA-2014-0292-0002

. (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) Fiberglas-Technik Rudolf Lindner GmbH & Co. KG Service Bulletin SB–G05, dated January 17, 2014.

(ii) Fiberglas-Technik Rudolf Lindner GmbH & Co. Fiberglas-Technik Rudolf Lindner GmbH & Co. KG Instructions A/I– G05, dated January 17, 2014.

(3) For Fiberglas-Technik Rudolf Lindner GmbH & Co. service information identified in this AD, contact Fiberglas-Technik Rudolf Lindner GmbH & Co. KG, Steige 3, D–88487 Walpertshofen, Germany; telephone: +49 (0) 7353/22 43; fax: +49 (0) 7353/30 96; email: info@LTB-Lindner.com ; Web site: http:// www.ltb-lindner.com/home.104.html

.

(4) You may view this service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

(5) You may view 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/cfr/ibrlocations.html

. Issued in Kansas City, Missouri, on July 14,
2014. Kelly A. Broadway, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014–17052 Filed 7–22–14; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0308; Directorate Identifier 2014–CE–012–AD; Amendment**  **39–17903; AD 2014–15–01]**

**RIN 2120–AA64**



### Airworthiness Directives; M7 **Aerospace LLC Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for M7 Aerospace LLC Models SA227–AT, SA227–AC, SA227–BC, SA227–CC, and SA227–DC airplanes equipped with a bayonet shear pin main cabin door latching mechanism. This AD was prompted by fatigue cracks found in the internal door surround doubler, the fuselage external skin, and the door corner fittings at the fuselage upper forward corner of the main cabin door cutout. This AD requires repetitively inspecting the four corners of the main cabin door cutout for cracks, making necessary repairs, and reporting inspection results to M7 Aerospace LLC. We are issuing this AD to correct the unsafe condition on these products.

**DATES** 

### : This AD is effective August 27,
2014.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 27, 2014.

**ADDRESSES** 

### : For service information identified in this AD, contact M7 Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: (210) 824–9421; fax: (210) 804–7766; Internet: http://www.elbitsystemsus.com ; email: MetroTech@ M7Aerospace.com . You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–
4148. Examining the AD Docket

You may examine the AD docket on the Internet at http://