This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

42949 

Vol. 77, No. 141 

Monday, July 23, 2012 

EXPORT-IMPORT BANK OF THE 

UNITED STATES 

12 CFR Part 404 

[EXIM–OIG–2012–0010] 

RIN 3048–AA02 

Privacy Act of 1974: Implementation of 

Exemptions; Export-Import Bank of the 

United States Office of Inspector 

General—EIB–35—Office of Inspector 

General Investigative Records; 

Correction 

AGENCY: Office of the Inspector General, 

Export-Import Bank of the United 

States. 

ACTION: Final rule; correction. 

SUMMARY: The Export-Import Bank of 

the United States (hereafter known as 

‘‘Ex-Im Bank’’) published in the Federal 

Register of July 17, 2012, a final rule to 

exempt portions of a system of records 

from one or more provisions of the 

Privacy Act. This document corrects an 

inaccurate amendatory instruction. 

DATES: Effective August 16, 2012. 

FOR FURTHER INFORMATION CONTACT: 

Osvaldo Gratacos, Ex-Im Bank, Office of 

Inspector General, 811 Vermont Avenue 

NW., Rm. 976, Washington, DC 20571 or 

by telephone (202) 565–3908 or 

facsimile (202) 565–3988. 

SUPPLEMENTARY INFORMATION: The Ex-Im 

Bank published a document on July 17, 

2012 (77 FR 41885–41886) exempting 

portions of a system of records entitled 

‘‘EIB–35—Office of Inspector General 

Investigative Records’’ from one or more 

provisions of the Privacy Act. The 

document incorrectly added § 404.24 to 

subpart B of 12 CFR part 404. Section 

404.24 currently exists in subpart C. The 

instruction should have revised 404.24, 

not added it. 

Accordingly, in rule FR Doc. 2012– 

17382 published on July 17, 2012 (77 FR 

41885–41886), make the following 

correction. 

1. On page 41886, in the first column, 

amendatory instruction 2 is corrected to 

read as follows: 

‘‘2. Section 404.24 is revised to read 

as follows:’’ 

Dated: July 17, 2012. 

Sharon A. Whitt, 

Agency Clearance Officer. 

[FR Doc. 2012–17896 Filed 7–20–12; 8:45 am] 

BILLING CODE 6690–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 23 

[Docket No. FAA–2012–0485; Special 

Conditions No. 23–258–SC] 

Special Conditions: Tamarack 

Aerospace Group, Cirrus Model SR22; 

Active Technology Load Alleviation 

System (ATLAS) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Tamarack Aerospace 

Group’s modification to the Cirrus SR22 

airplane. This airplane as modified by 

Tamarack will have a novel or unusual 

design feature(s) associated with 

Tamarack Aerospace Group’s 

modification. The design change will 

install winglets and an Active 

Technology Load Alleviation system 

(ATLAS). The addition of the ATLAS 

mitigates the negative effects of the 

winglets by effectively aerodynamically 

turning off the winglet under limit gust 

and maneuver loads. This is 

accomplished by measuring the aircraft 

loading and moving a small aileron-like 

device called a Tamarack Active Control 

Surface (TACS). The TACS movement 

reduces lift at the tip of the wing, 

resulting in the wing center of pressure 

moving inboard, thus reducing bending 

stresses along the wing span. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

These special conditions contain the 

additional safety standards that the 

Administrator considers necessary to 

establish a level of safety equivalent to 

that established by the existing 

airworthiness standards. 

DATES: Effective Date: July 13, 2013. 

FOR FURTHER INFORMATION CONTACT: For 

sections 23.301 through 23.629 

(structural requirements), contact Mr. 

Mike Reyer, telephone (816) 329–4131. 

For sections 23.672 through 23.701 

(control system requirements), contact 

Mr. Ross Schaller, telephone (816) 329– 

4162. The address and facsimile for both 

Mr. Reyer and Mr. Schaller is: Small 

Airplane Directorate, Aircraft 

Certification Service, 901 Locust, 

Kansas City, Missouri 64106; facsimile 

(816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Background 

On February 15, 2011, Tamarack 

Aerospace Group applied for a 

supplemental type certificate for 

installation of winglets and an Active 

Technology Load Alleviation System 

(ATLAS) on the Cirrus Model SR22 

(serial numbers 0002–2333, 2335–2419, 

and 2421–2437). The Cirrus Model SR22 

is a certified, single reciprocating 

engine, four-passenger, composite 

airplane. 

The installation of winglets, as 

proposed by Tamarack, increases 

aerodynamic efficiency. However, the 

winglets by themselves also increase 

wing static loads and the wing fatigue 

stress ratio, which under limit gust and 

maneuver loads factors may exceed the 

certificated wing design limits. The 

addition of ATLAS mitigates the 

negative effects of the winglets by 

effectively aerodynamically turning off 

the winglet at elevated gust and 

maneuver loads factors. 

The ATLAS functions as a load-relief 

system. This is accomplished by 

measuring aircraft loading via an 

accelerometer, and by moving a small 

aileron-like device called a Tamarack 

Active Control Surface (TACS) that 

reduces lift at the tip of the wing. 

Because the ATLAS compensates for the 

increased wing root bending at elevated 

load factors, the overall effect of this 

modification is that the winglet can be 

added to the Cirrus wing without the 

traditionally required reinforcement of 

the existing structure. This is the first 

application of an active loads alleviation 

system on a part 23 aircraft and the 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

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42950 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 

Type Certification Basis 

Under the provisions of § 21.101, 

Tamarack Aerospace Group must show 

that the Cirrus Model SR22, as changed, 

continues to meet the applicable 

provisions of the regulations 

incorporated by reference in Type 

Certificate Data Sheet A00009CH or the 

applicable regulations in effect on the 

date of application for the change. The 

regulations incorporated by reference in 

the type certificate are commonly 

referred to as the ‘‘original type 

certification basis.’’ The regulations 

incorporated by reference in Type 

Certificate Data Sheet A00009CH (Serial 

Numbers (S/Ns) 0002 through 2333, 

2335 through 2419, and 2421 through 

2437) are as follows: 

14 CFR part 23 of the Federal Aviation 

Regulations, effective February 1, 

1965, as amended by 23–1 through 

23–53, except as follows: 

14 CFR 23.301 through Amendment 

42 

14 CFR 23.855, 23.1326, 23.1359 not 

applicable 

14 CFR part 36, dated December 1, 

1969, as amended by 36–1 through 

36–22 

Except for: 

Increase in amendment level from the 

cirrus Model SR22 certification 

basis for Regulation 14 CFR 23.301 

through amendment 23–42 to: 14 

CFR 23.301 through Amendment 

23–48. 

Addition of regulation 14 CFR 23.1306 

through Amendment 23–61. 

Addition of regulation 14 CFR 23.1308 

through Amendment 23–57. 

Change in Cirrus Model SR22 

certification basis for regulation 14 

CFR 23.1359 through Amendment 

23–49 from: Not Applicable to: 

Applicable 

Equivalent Level of Safety (ELOS) 

Findings 

ACE–96–6 for 14 CFR Section 23.221 

(Spinning); refer to FAA 

Memorandum, dated June 10, 1998, 

for Models SR20, SR22. 

ACE–00–09 for 14 CFR 23.1143(g) 

(Engine Controls) and 23.1147(b) 

(Mixture Controls) Refer to FAA 

Memorandum, dated September 11, 

2000, for Model SR22. 

ACE–01–01 for 14 CFR 23.1143(g) 

(Engine Controls) and 23.1147(b) 

(Mixture Controls); Refer to FAA 

Memorandum, dated February 14, 

2001, for Model SR20. 

Special Conditions 

23–ACE–88 for ballistic parachute for 

Models SR20, SR22. 

23–134–SC for protection of systems 

for High Intensity Radiated Fields 

continued: (HIRF), for Models 

SR20, SR22. 

23–163–SC for inflatable restraint 

system. Addition to the certification 

basis Model SR20 effective S/N 

1541 and subsequent; Model SR22 

S/N 1500, 1520 and subsequent. 

In addition, if the regulations 

incorporated by reference do not 

provide adequate standards regarding 

the change, the applicant must comply 

with certain regulations in effect on the 

date of application for the change. The 

FAA has determined that the Cirrus 

SR22 complies with the following 

sections of 14 CFR part 23, as amended 

by Amendments 23–1 through 23–61 for 

the areas affected by the change. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 23) do not contain 

adequate or appropriate safety standards 

for the SR22 because of a novel or 

unusual design feature, special 

conditions are prescribed under the 

provisions of § 21.16. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the SR22 must comply with 

the fuel vent and exhaust emission 

requirements of 14 CFR part 35 and the 

noise certification requirements of 14 

CFR part 36. 

The FAA issues special conditions, as 

defined in § 11.19, in accordance with 

§ 11.38 and they become part of the type 

certification basis under § 21.101. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the applicant apply 

for a supplemental type certificate to 

modify any other model included on the 

same type certificate to incorporate the 

same novel or unusual design feature, 

the special conditions would also apply 

to the other model under § 21.101. 

Novel or Unusual Design Features 

The SR22 will incorporate the 

following novel or unusual design 

features: 

Winglets with an Active Technology 

Load Alleviation System (ATLAS) that 

incorporates a small aileron-like device 

called a Tamarack Active Control 

Surface (TACS). 

Discussion 

Tamarack has applied for a 

Supplemental Type Certificate to install 

a winglet and ATLAS. The ATLAS is 

not a primary flight control system, a 

trim device, or a wing flap. However, 

there is definite applicability to ATLAS 

for several regulations under part 23, 

Subpart D—Control Systems, which 

might otherwise be considered ‘‘Not 

Applicable’’ under a strict interpretation 

of the regulations. Other conditions may 

be developed, as needed, based on 

further FAA review and discussions 

with the manufacturer. 

Special conditions are also necessary 

for the effect of ATLAS on structural 

performance. These special conditions 

are intended to provide an equivalent 

level of safety for ATLAS as intended by 

part 23, Subpart C—Structure, and 

portions of part 23, Subpart D—Design 

and Construction. 

Discussion of Comments 

Notice of proposed special conditions 

No. 23–12–01–SC for the Cirrus SR22 

airplanes was published on May 15, 

2012 (77 FR 28530). No comments were 

received and the special conditions are 

adopted as proposed. 

Applicability 

As discussed above, these special 

conditions are applicable to the SR22 

(S/NS 0002 thru 2333, 2335 thru 2419, 

and 2421 thru 2437). Should Tamarack 

Aerospace Group apply at a later date 

for a supplemental type certificate to 

modify any other model included on 

Type Certificate Data Sheet A00009CH 

to incorporate the same novel or 

unusual design feature, the special 

conditions would apply to that model as 

well. 

Under standard practice, the effective 

date of final special conditions would 

be 30 days after the date of publication 

in the Federal Register; however, as the 

certification date for the Tamarack 

modified Cirrus SR22 is imminent, the 

FAA finds that good cause exists to 

make these special conditions effective 

upon issuance. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of airplane. It is not a rule of general 

applicability and it affects only the 

applicant who applied to the FAA for 

approval of these features on the 

airplane. 

List of Subjects in 14 CFR Part 23 

Aircraft, Aviation safety, Signs and 

symbols. 

■ The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for Cirrus Model SR22 

airplanes (S/Ns 0002 through 2333, 

2335 through 2419, and 2421 through 

2437) modified by Tamarack Aerospace 

Group. 

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Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 42951 

1. Active Load Alleviation Systems— 

Structural Requirements 

(A) The following special conditions 

apply to airplanes equipped with load 

alleviation systems that either directly, 

or as a result of failure or malfunction, 

affect structural performance. These 

special conditions address the direct 

structural consequences of the system 

responses and performances and cannot 

be considered in isolation but should be 

included in the overall safety evaluation 

of the airplane. Any statistical or 

probability terms used in the following 

special conditions apply to the 

structural requirements only and do not 

replace, remove, or supersede other 

requirements, including those in part 

23, subpart E. These criteria are only 

applicable to structure whose failure 

could prevent continued safe flight and 

landing. 

(B) In addition to the requirements in 

14 CFR part 23, § 23.301 Loads, comply 

with the following: 

SC 23.301 Loads, Probability of Failure 

of Load Alleviation System 

(a) Failures of the load alleviation 

system, including the annunciation 

system, must be immediately 

annunciated to the pilot or annunciated 

prior to the next flight. Failure of the 

load alleviation system, including the 

annunciation system, must be no greater 

than 1 × 10¥5 per flight hour. 

(b) If failure of the load alleviation 

system, including the annunciation 

system, is greater than 1 × 10¥8 per 

flight hour, an independent system 

functional test must be accomplished at 

a periodic interval to limit time 

exposure to an undetected failed 

system. The time interval for the system 

functional test must be selected so that 

the product of the time interval in hours 

and the failure of the load alleviation 

system, including the annunciation 

system, is no greater than 1 × 10¥5 per 

hour. 

(c) Failures of the load alleviation 

system, including the annunciation 

system, must be reported to the FAA in 

a manner acceptable to the 

Administrator. 

(C) In place of the requirements in 14 

CFR part 23, § 23.303 Factor of Safety, 

comply with the following: 

SC 23.303 Factor of Safety, Load 

Alleviation Systems 

The airplane must be able to 

withstand the limit and ultimate loads 

resulting from the following scenarios: 

(a) The loads resulting from 14 CFR 

part 23, §§ 23.321 through 23.537, as 

applicable, corresponding to a fully 

operative load alleviation system. A 

factor of safety of 1.5 must be applied 

to determine ultimate loads. 

(b) If an independent system 

functional test is required by SC 

23.301(b), the loads resulting from 14 

CFR part 23, §§ 23.321 through 23.537, 

as applicable, corresponding to the 

system in the failed state without 

additional flight limitations or 

reconfiguration of the airplane. A factor 

of safety of 1.0 must be applied to 

determine ultimate loads. 

(c) The loads corresponding to the 

time of occurrence of load alleviation 

system failure and immediately after the 

failure. These loads must be determined 

at any speed up to VNE, starting from 1g 

level flight conditions, and considering 

realistic scenarios, including pilot 

corrective actions. A factor of safety of 

1.5 must be applied to determine 

ultimate loads. 

(d) For airplanes equipped with 

‘‘before the next flight’’ failure 

annunciation systems, the loads 

resulting from 14 CFR part 23, §§ 23.321 

through 23.537, as applicable, 

corresponding to the system in the 

failed state without additional flight 

limitations or reconfiguration of the 

airplane. A factor of safety of 1.25 must 

be applied to determine ultimate loads. 

(e) For airplanes equipped with 

‘‘immediate’’ failure annunciation 

systems, the loads resulting from 14 

CFR part 23, §§ 23.321 through 23.537, 

as applicable, corresponding to the 

system in the failed state with 

additional flight limitations or 

reconfiguration of the airplane. A factor 

of safety of 1.0 must be applied to 

determine ultimate loads. 

(D) In addition to the requirements in 

14 CFR part 23, §§ 23.571 through 

23.574, comply with the following: 

SC 23.571 Through SC 23.574 Fatigue 

and Damage Tolerance 

If any system failure would have a 

significant effect on the fatigue or 

damage evaluations required in 

§§ 23.571 through 23.574, then these 

effects must be taken into account. If an 

independent system functional test is 

required by SC 23.301(b), the effect on 

fatigue and damage evaluations 

resulting from the selected inspection 

interval must be taken into account. 

(E) In addition to the requirements in 

14 CFR part 23, § 23.629 Flutter, comply 

with the following: 

SC 23.629 Flutter 

(a) With the load alleviation system 

fully operative, compliance to 14 CFR 

part 23, § 23.629 must be shown. 

Compliance with § 23.629(f) must 

include the ATLAS control system and 

control surface. 

(b) At the time of occurrence of load 

alleviation system failure and 

immediately after the failure, 

compliance with 14 CFR part 23, 

§ 23.629(a) and (e) must be shown up to 

VD/MD without consideration of 

additional operating limitations or 

reconfiguration of the airplane. 

(c) For airplanes equipped with 

‘‘before the next flight’’ failure 

annunciation systems and the load 

alleviation system in the failed state, 

compliance to 14 CFR part 23, § 23.629 

Flutter, paragraphs (a) and (e), must be 

shown up to VD/MD without 

consideration of additional operating 

limitations or reconfiguration of the 

airplane. 

(d) For airplanes equipped with 

‘‘immediate’’ failure annunciation 

systems and the load alleviation system 

in the failed state, compliance to 14 CFR 

part 23, § 23.629 Flutter, paragraphs (a) 

and (e), must be shown with 

consideration of additional operating 

limitations or reconfiguration of the 

airplane at speeds up to VD = 1.4 × 

maximum speed limitation selected by 

the applicant. 

2. Active Load Alleviation Systems— 

Control System Requirements. 

(A) In place of 14 CFR part 23, 

§ 23.672 Stability augmentation and 

automatic and power-operated systems 

requirement, comply with the following: 

SC 23.672 Load Alleviation Systems 

The load alleviation system must 

comply with the following: 

(a) A warning, which is clearly 

distinguishable to the pilot under 

expected flight conditions without 

requiring the pilot’s attention, must be 

provided for any failure in the load 

alleviation system or in any other 

automatic system that could result in an 

unsafe condition if the pilot was not 

aware of the failure. Warning systems 

must not activate the control system. 

(b) The design of the load alleviation 

system or of any other automatic system 

must permit initial counteraction of 

failures without requiring exceptional 

pilot skill or strength, by either the 

deactivation of the system or a failed 

portion thereof, or by overriding the 

failure by movement of the flight 

controls in the normal sense. 

(c) It must be shown that, while the 

system is active or after any single 

failure of the load alleviation system— 

(1) The airplane is safely controllable 

when the failure or malfunction occurs 

at any speed or altitude within the 

approved operating limitations that is 

critical for the type of failure being 

considered; 

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42952 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 

(2) The controllability and 

maneuverability requirements of this 

part are met within a practical 

operational flight envelope (for 

example, speed, altitude, normal 

acceleration, and airplane configuration) 

that is described in the Airplane Flight 

Manual (AFM); and 

(3) The trim, stability, and stall 

characteristics are not impaired below a 

level needed to permit continued safe 

flight and landing. 

(B) In place of 14 CFR part 23, 

§ 23.677 Trim systems requirement, 

comply with the following: 

SC 23.677 Load Alleviation Active 

Control Surface 

(a) Proper precautions must be taken 

to prevent inadvertent, improper, or 

abrupt Tamarack Active Control Surface 

(TACS) operation. 

(b) The load alleviation system must 

be designed so that, when any one 

connecting or transmitting element in 

the primary flight control system fails, 

adequate longitudinal control for safe 

flight and landing is available. 

(c) The load alleviation system must 

be irreversible unless the TACS is 

properly balanced and has no unsafe 

flutter characteristics. The system must 

have adequate rigidity and reliability in 

the portion of the system from the tab 

to the attachment of the irreversible unit 

to the airplane structure. 

(d) It must be demonstrated that the 

airplane is safely controllable and that 

the pilot can perform all maneuvers and 

operations necessary to effect a safe 

landing following any probable powered 

system runaway that reasonably might 

be expected in service, allowing for 

appropriate time delay after pilot 

recognition of the system runaway. The 

demonstration must be conducted at 

critical airplane weights and center of 

gravity positions. 

(C) In place of 14 CFR part 23, 

§ 23.683 Operation tests requirement, 

comply with the following: 

SC 23.683 Operation tests 

(a) It must be shown by operation 

tests that, when the load alleviation 

system is active and operational and 

loaded as prescribed in paragraph (b) of 

this section, the system is free from— 

(1) Jamming; 

(2) Excessive friction; and 

(3) Excessive deflection. 

(b) The prescribed test loads are, for 

the entire system, loads corresponding 

to the limit airloads on the appropriate 

surface. 

(D) In place of 14 CFR part 23, 

§ 23.685 Control system details 

requirement, comply with the following: 

SC 23.685 Control System Details 

(a) Each detail of the Tamarack Active 

Control Surface (TACS) must be 

designed and installed to prevent 

jamming, chafing, and interference from 

cargo, passengers, loose objects, or the 

freezing of moisture. 

(b) There must be means in the 

cockpit to prevent the entry of foreign 

objects into places where they would 

jam any one connecting or transmitting 

element of the system. 

(c) Each element of the load 

alleviation system must have design 

features, or must be distinctively and 

permanently marked, to minimize the 

possibility of incorrect assembly that 

could result in malfunctioning of the 

control system. 

(E) In place of 14 CFR part 23, 

§ 23.697 Wing flap controls 

requirement, comply with the following: 

SC 23.697 Load Alleviation System 

Controls 

(a) The Tamarack Active Control 

Surface (TACS) must be designed so 

that, when the surface has been placed 

in any position, it will not move from 

that position unless the control is 

adjusted or is moved by the automatic 

operation of a load alleviation system. 

(b) The rate of movement of the TACS 

in response to the automatic device 

must give satisfactory flight and 

performance characteristics under 

steady or changing conditions of 

airspeed, engine power, and attitude. 

(F) In place of 14 CFR part 23, 

§ 23.701 Flap interconnection 

requirement, comply with the following: 

SC 23.701 Load Alleviation System 

Interconnection 

(a) The load alleviation system and 

related movable surfaces as a system 

must— 

(1) Be synchronized by a mechanical 

interconnection between the movable 

surfaces; or by an approved equivalent 

means; or 

(2) Be designed so that the occurrence 

of any failure of the system that would 

result in an unsafe flight characteristic 

of the airplane is extremely improbable; 

or 

(b) The airplane must be shown to 

have safe flight characteristics with any 

combination of extreme positions of 

individual movable surfaces. 

Issued in Kansas City, Missouri, on July 13, 

2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–17864 Filed 7–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0329; Directorate 

Identifier 2011–NM–139–AD; Amendment 

39–17127; AD 2012–14–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318–112 and –121 

airplanes; Model A319–111, –112, –115, 

–132, and –133 airplanes; Model A320– 

214, –232, and –233 airplanes; and 

Model A321–211, –212, –213, and –231 

airplanes. This AD was prompted by 

reports of some fuselage nuts found 

cracked. This AD requires an inspection 

to determine if certain fuselage nuts are 

installed, a detailed inspection for 

cracking of fuselage nuts having a 

certain part number, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct fuselage nuts found 

cracked, which could result in reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

August 27, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 27, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 2, 2012 (77 FR 19567). 

That NPRM proposed to correct an 

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