Federal Register / Vol. 77, No. 127 / Monday, July 2, 2012 / Rules and Regulations 39153 

PART 915—AVOCADOS GROWN IN 

SOUTH FLORIDA 

■ 1. The authority citation for 7 CFR 

part 915 continues to read as follows: 

Authority: 7 U.S.C. 601–674. 

■ 2. Section 915.235 is revised to read 

as follows: 

§ 915.235 Assessment rate. 

On and after April 1, 2012, an 

assessment rate of $0.25 per 55-pound 

container or equivalent is established 

for avocados grown in South Florida. 

Dated: June 26, 2012. 

David R. Shipman, 

Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2012–16063 Filed 6–29–12; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0673; Directorate 

Identifier 2012–NM–091–AD; Amendment 

39–17109; AD 2012–13–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This AD requires inspecting 

parts or doing a records review to 

determine if certain trailing edge flap 

carriages are installed, doing repetitive 

inspections for corrosion, and flaking or 

missing thermal coating on suspect 

carriage spindles, and related 

investigative and corrective actions, if 

necessary; this AD also provides 

optional terminating action for the 

repetitive inspections. This AD was 

prompted by reports of corrosion found 

on carriage that are located on the 

outboard flaps. We are issuing this AD 

to detect and correct corrosion of the 

carriage spindle, which could result in 

a fracture; fracture of both the inboard 

and outboard carriage spindles, at the 

forward ends through the large 

diameters, on a single flap assembly, 

could adversely affect the continued 

safe flight and landing of the airplane. 

DATES: This AD is effective July 17, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 17, 2012. 

We must receive comments on this 

AD by August 16, 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 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; 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 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6440; fax: (425) 917–6590; email: 

Nancy.Marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received reports of corrosion 

found on carriages that are located on 

the outboard flaps. Each of the suspect 

carriages had accumulated fewer than 

7,000 total flight cycles. The suspect 

carriages had tungsten-carbide-cobaltchrome coating applied with high 

velocity oxygenated fuel (HVOF) 

thermal coating on the spindle. The 

HVOF thermal coating had flaked off the 

lower surface of the spindle, at the root 

of the spindle. Cracked, flaking, or 

missing thermal coating can lead to 

moisture ingress, which might begin 

corroding the alloy steel base metal. 

Corrosion pits in this area could create 

a stress concentration where a crack can 

start in the base metal, resulting in the 

inability of the carriage to sustain limit 

load. Corrosion of the carriage spindle, 

if not detected and corrected, could 

result in fracture of the spindle. One 

fractured carriage spindle on a flap can 

be compensated for with pilot inputs to 

the aileron or rudder (increasing pilot 

workload). However, fracture of both the 

inboard and outboard carriage spindles, 

at the forward ends through the large 

diameters, on a single flap, could 

adversely affect the continued safe flight 

and landing of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–57A1319, dated April 16, 

2012, as revised by Boeing Alert Service 

Bulletin 737–57A1319, Revision 1, 

dated June 6, 2012. This service 

information describes the following 

procedures. 

• For all airplanes, inspection of parts 

or review of maintenance records to 

determine if a carriage, i.e., a carriage 

with HVOF thermal coating, is installed 

at wing butt line (WBL) 254 or WBL 

355. 

• For any suspect carriage or carriage 

with an unidentifiable part number 

(P/N): Repetitive detailed inspections 

for corrosion, missing, or flaking 

thermal coating on the forward end of 

the carriage spindle at the root (with the 

option to do a borescope inspection 

instead), and related investigative and 

corrective actions if necessary. 

• Related investigative action is a 

detailed inspection for corrosion 

inhibiting compound (CIC) coverage on 

the lower surface of the spindle at the 

root. 

• The corrective actions include 

applying or reapplying CIC, and 

replacing the suspect carriage with a 

new or serviceable carriage. 

• Replacement of the suspect carriage 

with a new or serviceable non-HVOF 

thermal coated carriage eliminates the 

need for the repetitive inspections for 

that carriage only. 


pmangrum on DSK3VPTVN1PROD with RULES
39154 Federal Register / Vol. 77, No. 127 / Monday, July 2, 2012 / Rules and Regulations 

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 the same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously. 

Interim Action 

We consider this AD interim action. 

The manufacturer is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

might consider additional rulemaking. 

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 corrosion occurring on the 

exposed base metal can quickly lead to 

cracking and full fracture of the carriage 

spindle. Fracture of both the inboard 

and outboard carriage spindles, in the 

forward ends through the large 

diameters, on a single flap, could 

adversely affect the continued safe flight 

and landing of the airplane. Because of 

our requirement to promote safe flight of 

civil aircraft and thus, the critical need 

to assure the structural integrity of the 

carriage spindle and the short 

compliance time involved with this 

action, this AD must be issued 

immediately. 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–2012–0673 and Directorate 

Identifier 2012–NM–091–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 494 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Number of 

U.S. operators 

Cost on U.S. 

operators 

Inspection or records review to determine installation of 

suspect carriage ............................................................... 1 work-hour × 

$85 per hour = 

$85 

$0 $85 494 $41,990 

We estimate the following costs to do 

any necessary actions that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these actions. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Inspection of suspect carriages ..... 3 work-hours × $85 per hour = 

$255 per inspection cycle.

$0 .................................................. $255 per inspection cycle. 

Replacement of carriage spindle, 

per spindle (four spindles per airplane).

17 work-hours × $85 per hour = 

$1,445.

We have received no definitive 

data that would enable us to 

provide a cost estimate for parts 

necessary for the replacement 

specified in this AD.

$1,445. 

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: 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 77, No. 127 / Monday, July 2, 2012 / Rules and Regulations 39155 

(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, 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): 

2012–13–07 The Boeing Company: 

Amendment 39–17109; Docket No. 

FAA–2012–0673; Directorate Identifier 

2012–NM–091–AD. 

(a) Effective Date 

This AD is effective July 17, 2012. 

(b) Affected ADs 

This AD affects AD 2011–04–10, 

Amendment 39–16609 (76 FR 9498, February 

18, 2011). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

corrosion found on carriage spindles that are 

located on the outboard flaps. We are issuing 

this AD to detect and correct corrosion of the 

carriage spindle, which could result in a 

fracture; fracture of both the inboard and 

outboard carriage spindles, at the forward 

ends through the large diameters, on a single 

flap, could adversely affect the continued 

safe flight and landing of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection To Determine Suspect 

Carriage Spindle 

Within 90 days after the effective date of 

this AD, do an inspection of the part or a 

records review to determine whether a 

suspect carriage with a high velocity 

oxygenated fuel (HVOF) thermal coating is 

installed at wing butt line (WBL) 254 or WBL 

355, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1319, dated April 16, 2012, as 

revised by Boeing Alert Service Bulletin 

737–57A1319, Revision 1, dated June 6, 

2012. If no suspect carriage is installed, no 

further action is required by this paragraph. 

(h) Repetitive Inspections, Related 

Investigative Actions, and Corrective Action 

(1) For airplanes on which any suspect 

carriage is installed, or if the part number of 

the carriage cannot be determined: Within 90 

days after the effective date of this AD, or 

within 180 days after installation of a suspect 

carriage, whichever occurs later, do a 

detailed or borescope inspection of the 

forward end of the carriage spindle for 

corrosion and flaking and missing thermal 

coating, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1319, dated April 16, 2012, as 

revised by Boeing Alert Service Bulletin 

737–57A1319, Revision 1, dated June 6, 

2012. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the detailed or borescope inspection 

thereafter at intervals not to exceed 180 days. 

(2) For the purposes of this AD, a 

‘‘serviceable part’’ can be either a suspect 

part (i.e., a carriage with HVOF thermal 

coating) or a non-suspect part (i.e., a carriage 

that does not have HVOF thermal coating). 

(i) Optional Terminating Action 

Replacement of a suspect carriage with a 

new or serviceable carriage without HVOF 

thermal coating, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–57A1319, dated April 

16, 2012, as revised by Boeing Alert Service 

Bulletin 737–57A1319, Revision 1, dated 

June 6, 2012, terminates the requirements of 

paragraph (h) of this AD for that carriage 

spindle only. 

(j) Parts Installation 

As of the effective date of this AD, a 

serviceable HVOF-coated carriage may not be 

installed on an airplane unless the actions 

required by paragraph (h)(1) of this AD are 

done on that carriage prior to installation. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

inspections required by paragraphs (g) and 

(h) of this AD, and the replacement specified 

in paragraph (i) of this AD, if those actions 

were performed before the effective date of 

this AD using Boeing Alert Service Bulletin 

737–57A1319, dated April 16, 2012. 

(l) 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: 9-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. 

(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) The inspection required by paragraph 

(h) of this AD may be used as an AMOC for 

the initial and repetitive detailed or 

borescope inspections required by 

paragraphs (h) and (i) of AD 2011–04–10, 

Amendment 39–16609 (76 FR 9498, 

February 18, 2011), provided the inspections 

are accomplished at the compliance times 

required by that AD. 

(m) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: (425) 917–6440; fax: (425) 917– 

6590; email: Nancy.Marsh@faa.gov. 

(n) 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) Boeing Alert Service Bulletin 737– 

57A1319, dated April 16, 2012. 

(ii) Boeing Alert Service Bulletin 737– 

57A1319, Revision 1, dated June 6, 2012. 

(3) 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; Internet https:// 

www.myboeingfleet.com. 

(4) You may review copies of the 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. 

(5) You may also review copies of the 

service information that is incorporated by 


pmangrum on DSK3VPTVN1PROD with RULES
39156 Federal Register / Vol. 77, No. 127 / Monday, July 2, 2012 / Rules and Regulations 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on June 21, 

2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–15898 Filed 6–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0224; Directorate 

Identifier 2007–NE–44–AD; Amendment 39– 

17085; AD 2009–07–01 R1] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG (RRD) 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; rescission. 

SUMMARY: We are rescinding an 

airworthiness directive (AD) for RRD 

BR700–715A1–30, BR700–715B1–30, 

and BR700–715C1–30 turbofan engines. 

The existing AD resulted from the need 

to reduce the published life limits of 

high-pressure (HP) turbine stage 1 discs, 

part numbers (P/Ns) BRH20130 and 

BRH20131, and HP turbine stage 2 

discs, P/Ns BRH19423 and BRH19427. 

We are rescinding the existing AD 

because RRD has revised the approved 

published life limits of these parts to the 

same or higher limits as originally 

certified. 

DATES: This AD is effective August 6, 

2012. 

ADDRESSES: 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: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7758; fax: 781–238– 

7199; email: mark.riley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to rescind an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on February 21, 2012 (77 FR 

9869). That NPRM proposed to rescind 

AD 2009–07–01 (74 FR 12086, March 

23, 2009) for RRD BR700–715A1–30, 

BR700–715B1–30, and BR700–715C1– 

30 turbofan engines. AD 2009–07–01 

resulted from the need to reduce the 

published life limits of HP turbine stage 

1 discs, P/Ns BRH20130 and BRH20131, 

and HP turbine stage 2 discs, P/Ns 

BRH19423 and BRH19427. We are 

rescinding that AD because RRD has 

revised the approved published life 

limits of these parts to the same or 

higher limits as originally certified. We 

evaluated all information and 

determined that allowing the increase in 

the published part life limits is 

acceptable. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 9869, February 21, 2012). 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 

rescinding airworthiness directive (AD) 

2009–07–01, Amendment 39–15860 (74 

FR 12086, March 23, 2009): 

2009–07–01 R1 Rolls-Royce Deutschland 

Ltd & Co KG (formerly BMW RollsRoyce GmbH, formerly BMW RollsRoyce Aero Engines): Amendment 39– 

17085; Docket No. FAA–2008–0224; 

Directorate Identifier 2007–NE–44–AD. 

(a) Effective Date 

This AD is effective August 6, 2012. 

(b) Affected ADs 

This AD rescinds AD 2009–07–01 (74 FR 

12086, March 23, 2009). 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG BR700–715A1–30, 

BR700–715B1–30, and BR700–715C1–30 

turbofan engines. 


pmangrum on DSK3VPTVN1PROD with RULES