44434 Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Rules and Regulations 

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: 

2012–15–06 Gulfstream Aerospace LP 

(Type Certificate Previously Held by 

Israel Aircraft Industries, Ltd.): 

Amendment 39–17135. Docket No. 

FAA–2010–1164; Directorate Identifier 

2010–NM–057–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 4, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Gulfstream Aerospace 

LP (Type Certificate previously held by Israel 

Aircraft Industries, Ltd.) Model Astra SPX, 

1125 Westwind Astra, and Gulfstream 100 

airplanes, serial numbers 002 through 158 

inclusive, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Reason 

This AD was prompted by a report 

indicating that sponge rubber padding was 

found between wheel well fuel lines and 

electrical harnesses. We are issuing this AD 

to detect and correct corrosion or chafing of 

the fuel lines, which could result in fuel 

leakage and possible fire in the wheel well 

area. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Actions 

Within 24 months after the effective date 

of this AD, inspect for the presence of sponge 

rubber padding on the fuel lines in the wheel 

well area and inspect the fuel lines and 

electrical harnesses in the wheel well area for 

proper separation, in accordance with the 

Accomplishment Instructions of Gulfstream 

Service Bulletin 100–28–297, dated January 

21, 2010. 

(1) If any sponge rubber padding is found, 

before further flight, remove all sponge 

rubber padding from the fuel lines, inspect 

the fuel lines that were covered with the 

rubber padding for any corrosion and repair 

or replace as applicable any corroded or 

chafed fuel lines, in accordance with the 

Accomplishment Instructions of Gulfstream 

Service Bulletin 100–28–297, dated January 

21, 2010. 

(2) If any fuel lines and electrical harnesses 

are found to not have proper separation, 

before further flight, install loop clamps in 

accordance with the Accomplishment 

Instructions of Gulfstream Service Bulletin 

100–28–297, dated January 21, 2010. 

(3) If proper separation is found, and no 

sponge rubber padding is found, no further 

action is required by this paragraph. 

(h) 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: 

Tom Groves, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1503; 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) 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. 

(i) Related Information 

Refer to MCAI Israeli Airworthiness 

Directive 28–10–02–01, dated February 22, 

2010; and Gulfstream Service Bulletin 100– 

28–297, dated January 21, 2010; for related 

information. 

(j) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 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: 

(i) Gulfstream Service Bulletin 100–28– 

297, dated January 21, 2010. 

(ii) Reserved. 

(2) For service information identified in 

this AD, contact Gulfstream Aerospace 

Corporation, P.O. Box 2206, Mail Station 

D–25, Savannah, Georgia 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. 

(3) 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. 

(4) 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 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 July 17, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–18153 Filed 7–27–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0488; Directorate 

Identifier 2008–SW–20–AD; Amendment 39– 

17126; AD 2012–14–12] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Restricted Category Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Arrow 

Falcon Exporters, Inc. (previously Utah 

State University); Firefly Aviation 

Helicopter Services (previously 

Erickson Air-Crane Co.); California 

Department of Forestry; Garlick 

Helicopters, Inc.; Global Helicopter 

Technology, Inc.; Hagglund Helicopters, 

LLC (previously Western International 

Aviation, Inc.); International 

Helicopters, Inc.; Precision Helicopters, 

LLC; Robinson Air Crane, Inc.; San 

Joaquin Helicopters (previously 

Hawkins and Powers Aviation, Inc.); 

S.M.&T. Aircraft (previously US 

Helicopters, Inc., UNC Helicopter, Inc., 

Southern Aero Corporation, and Wilco 

Aviation); Smith Helicopters; Southern 

Helicopter, Inc.; Southwest Florida 

Aviation International, Inc. (previously 

Jamie R. Hill and Southwest Florida 

Aviation); Tamarack Helicopters, Inc. 

(previously Ranger Helicopter Services, 

Inc.); US Helicopter, Inc. (previously 

UNC Helicopter, Inc.); West Coast 

Fabrication; and Williams Helicopter 

Corporation (previously Scott Paper Co.) 

Model HH–1K, TH–1F, TH–1L, UH–1A, 

UH–1B, UH–1E, UH–1F, UH–1H, UH– 

1L, and UH–1P Helicopters; and 

Southwest Florida Aviation Model UH– 

1B (SW204 and SW204HP) and UH–1H 

(SW205) Helicopters. This AD requires 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Rules and Regulations 44435 

inspecting each affected tail rotor blade 

(blade) forward tip weight retention 

block (tip block) and the aft tip closure 

(tip closure) for adhesive bond voids 

and removing any blade with an 

excessive void from service. This AD 

also requires modifying certain blades 

by installing shear pins and tip closure 

rivets. This AD was prompted by reports 

of missing tip blocks or tip closures, 

resulting in minor to substantial damage 

to blades installed on Bell Model 212 

and 412 helicopters. The actions are 

intended to prevent loss of a tip block 

or tip closure, loss of a blade, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective September 4, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of September 4, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 

280–3391; fax (817) 280–6466; or at 

http://www.bellcustomer.com/files/. 

You may review a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

Examining the AD Docket: You may 

examine the AD docket on the Internet 

at http://www.regulations.gov or in 

person at the Docket Operations Office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aviation Safety 

Engineer, Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5170; email 

7-avs-asw-170@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 13, 2010, at 75 FR 26889, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

Arrow Falcon Exporters, Inc. 

(previously Utah State University); 

Firefly Aviation Helicopter Services 

(previously Erickson Air-Crane Co.); 

California Department of Forestry; 

Garlick Helicopters, Inc.; Global 

Helicopter Technology, Inc.; Hagglund 

Helicopters, LLC (previously Western 

International Aviation, Inc.); 

International Helicopters, Inc.; Precision 

Helicopters, LLC; Robinson Air Crane, 

Inc.; San Joaquin Helicopters 

(previously Hawkins and Powers 

Aviation, Inc.); S.M.&T. Aircraft 

(previously US Helicopters, Inc., UNC 

Helicopter, Inc., Southern Aero 

Corporation, and Wilco Aviation); 

Smith Helicopters; Southern Helicopter, 

Inc.; Southwest Florida Aviation 

International, Inc. (previously Jamie R. 

Hill and Southwest Florida Aviation); 

Tamarack Helicopters, Inc. (previously 

Ranger Helicopter Services, Inc.); US 

Helicopter, Inc. (previously UNC 

Helicopter, Inc.); West Coast 

Fabrication; and Williams Helicopter 

Corporation (previously Scott Paper Co.) 

Model HH–1K, TH–1F, TH–1L, UH–1A, 

UH–1B, UH–1E, UH–1F, UH–1H, UH– 

1L, and UH–1P Helicopters; and 

Southwest Florida Aviation Model UH– 

1B (SW204 and SW204HP) and UH–1H 

(SW205) Helicopters. This NPRM 

proposed to require inspecting each 

applicable blade tip block and tip 

closure for voids and removing any 

blade with an excessive void from 

service. The NPRM also proposed to 

require modifying certain blades by 

installing shear pins and tip closure 

rivets. The proposed requirements were 

intended to prevent loss of a tip block 

or tip closure, loss of a blade, and 

subsequent loss of control of the 

helicopter. 

AD 2002–09–04, Amendment 39– 

12737 (67 FR 22349, May 3, 2002), was 

issued for the Bell Model 205A, 205A– 

1, 205B, 212, 412, 412CF, and 412EP 

helicopters and contained the same 

requirements as those in this AD. AD 

2007–22–02, Amendment 39–15238 (72 

FR 60760, October 26, 2007), 

superseded AD 2002–09–04 to expand 

the applicability to include other partand serial-numbered blades. Some of 

the blades in the applicability of AD 

2007–22–02 are eligible for installation 

on helicopters included in this AD, 

which may have an FAA-approved 

modification that increases the 

helicopter’s power rating to the 

equivalent of the Bell Model 205B or the 

212 helicopter. The Bell Model 205B 

and 212 helicopters are addressed in AD 

2007–22–02. Consequently, the 

inspections and modifications required 

by AD 2007–22–02 are mandated for the 

blades installed on helicopters included 

in this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed except we have revised the 

estimated costs of complying with this 

AD to reflect ten hours for inspection 

instead of three hours, and minor 

editorial changes. These minor editorial 

changes are consistent with the intent of 

the proposals in the NPRM and will not 

increase the scope of the AD. 

Related Service Information 

We have reviewed Bell Helicopter 

Textron Alert Service Bulletin No. 212– 

00–111, Revision D, dated March 18, 

2005 (ASB), which describes procedures 

for inspecting and modifying certain tail 

rotor blades. The ASB was issued as a 

result of an investigation of an in-flight 

loss of a blade tip block, part number (P/ 

N) 212–010–750–105. The investigation 

revealed the countersunk screws 

retaining the tip block were installed 

incorrectly, resulting in inadequate tip 

block retention. Reports have also been 

submitted about loss of the tip closures 

from other blades possibly because of 

inadequate adhesive bonding in this 

area. 

Costs of Compliance 

We estimate that this AD will affect 

716 helicopters of U.S. registry, and 25 

of those helicopters will have the 

increased power rating. Labor costs will 

average an estimated $85 per work hour. 

Based on these assumptions, we expect 

the following costs: 

• About 1 work hour to review the 

helicopter records for a labor cost of $85 

per helicopter, $60,860 for the U.S. fleet. 

• About 10 work hours to inspect the 

affected blades, install the shear pins 

and tip closure rivets, reidentify, and 

dynamically balance the blade. 

Required supplies will cost about $45, 

for a total cost of $895 per helicopter. 

We assume that the blade sets are 

installed on 25 helicopters with the 

FAA-approved modification that will 

need to be inspected and repaired. 


tkelley on DSK3SPTVN1PROD with RULES
44436 Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Rules and Regulations 

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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2012–14–12 Arrow Falcon Exporters, Inc. 

(previously Utah State University); 

Firefly Aviation Helicopter Services 

(previously Erickson Air-Crane Co.); 

California Department of Forestry; 

Garlick Helicopters, Inc.; Global 

Helicopter Technology, Inc.; Hagglund 

Helicopters, LLC (previously Western 

International Aviation, Inc.); 

International Helicopters, Inc.; Precision 

Helicopters, LLC; Robinson Air Crane, 

Inc.; San Joaquin Helicopters 

(previously Hawkins and Powers 

Aviation, Inc.); S.M.&T. Aircraft 

(previously US Helicopters, Inc., UNC 

Helicopter, Inc., Southern Aero 

Corporation, and Wilco Aviation); Smith 

Helicopters; Southern Helicopter, Inc.; 

Southwest Florida Aviation 

International, Inc. (previously Jamie R. 

Hill and Southwest Florida Aviation); 

Tamarack Helicopters, Inc. (previously 

Ranger Helicopter Services, Inc.); US 

Helicopter, Inc. (previously UNC 

Helicopter, Inc.); West Coast 

Fabrication; and Williams Helicopter 

Corporation (previously Scott Paper Co.) 

Model HH–1K, TH–1F, TH–1L, UH–1A, 

UH–1B, UH–1E, UH–1F, UH–1H, UH–1L, 

and UH–1P Helicopters; and Southwest 

Florida Aviation Model UH–1B (SW204 

and SW204HP) and UH–1H (SW205) 

Helicopters: Amendment 39–17126; 

Docket No. FAA–2010–0488; Directorate 

Identifier 2008–SW–20–AD. 

(a) Applicability 

(1) This AD applies to Model HH–1K, TH– 

1F, TH–1L, UH–1A, UH–1B, UH–1E, UH–1F, 

UH–1H, UH–1L, and UH–1P helicopters, and 

Southwest Florida Aviation Model UH–1B 

series (SW204 series and SW204HP) and 

UH–1H series (SW205 series) helicopters, 

with a tail rotor blade (blade), part number 

(P/N) 212–010–750–009 through –129, all 

serial numbers except serial numbers with a 

prefix of ‘‘A’’ or ‘‘AFS,’’ and the number 

11926, 13351, 13367, 13393, 13400, 13402, 

13515, 13540, 13568, 13595 through 13602, 

13619, and subsequent larger numbers, 

installed, certificated in any category. 

(2) A blade inspected and modified by 

following either AD 2002–09–04 (67 FR 

22349, May 3, 2002) or AD 2007–22–02 (72 

FR 60760, October 26, 2007), for the Bell 

Helicopter Textron (Bell) Model 205A, 205A– 

1, 205B, 212, 412, 412CF, and 412EP 

helicopters satisfies the requirements of this 

AD. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

adhesive bond voids. This condition could 

result in loss of the forward tip weight 

retention block (tip block) or aft tip closure 

(tip closure), loss of the blade, and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective September 4, 

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 100 hours time-in-service: 

(1) Inspect the tip block and tip closure of 

each blade for voids. Remove from service 

any blade with a void in excess of that 

allowed by the applicable maintenance or 

Component Repair and Overhaul Manual 

limitations. 

(2) Inspect the tip block attachment 

countersink screws in the four locations to 

determine if the head of each countersunk 

screw is flush with the surface of the 

abrasion strip. The locations of these four 

screws are depicted on Figure 1 of Bell Alert 

Service Bulletin 212–00–111, Revision D, 

dated March 18, 2005 (ASB). If any of these 

screws are set below the surface of the 

abrasion strip or are covered with filler 

material, install shear pins by following the 

Accomplishment Instructions, Part A, Shear 

Pin Installation paragraphs, of the ASB. 

(3) Install the tip closure rivets on each 

blade, re-identify the modified blade by 

adding an ‘‘FM’’ after the P/N, and 

dynamically balance the tail rotor hub 

assembly by following the Accomplishment 

Instructions, Part B, Aft Tip Closure Rivet 

Installation paragraphs, of the ASB. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, Rotorcraft Directorate, FAA, may 

approve AMOCs for this AD. Send your 

proposal to: Michael Kohner, Aviation Safety 

Engineer, Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone 

(817) 222–5170; email 7-avs-asw170@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. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail Rotor Blades. 

(h) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Bell Helicopter Textron Alert Service 

Bulletin No. 212–00–111, Revision D, dated 

March 18, 2005. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 146 / Monday, July 30, 2012 / Rules and Regulations 44437 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, TX 76101; 

telephone (817) 280–3391; fax (817) 280– 

6466; or at http://www.bellcustomer.com/ 

files/. 

(4) You may review the referenced 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 a copy 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on July 10, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–17607 Filed 7–27–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1251; Directorate 

Identifier 2011–NM–017–AD; Amendment 

39–17132; AD 2012–15–03] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Embraer S.A. Model ERJ 190 airplanes. 

This AD was prompted by a report of 

damage on the rod end of the retracting 

actuator rod of the main landing gear 

(MLG). This AD requires performing a 

one-time general visual inspection to 

determine if a certain part number is 

installed on the MLG retraction 

actuator; if necessary, performing a 

general visual inspection for 

discrepancies between the actuator rod 

end and shock strut lug of the MLG 

retraction actuator; and corrective 

actions if necessary. We are issuing this 

AD to detect and correct breakage of the 

MLG retracting actuator rod, which may 

result in MLG extension with no 

hydraulic damping and consequent 

damage to the locking mechanism and 

collapse of the MLG. 

DATES: This AD becomes effective 

September 4, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 4, 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: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2768; 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 November 28, 2011 (76 FR 

72855). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

It has been found the occurrence of damage 

on the rod end of the Main Landing Gear 

(MLG) retraction actuator. The ANAC 

[Ageˆncia Nacional de Aviac ̧a ̃o Civil] is 

issuing this AD to prevent breakage of the 

MLG retracting actuator rod, which may 

result in MLG extension with no hydraulic 

damping and consequent damage to the 

locking mechanism and collapse of the MLG. 

* * * * * 

Required actions include a one-time 

general visual inspection to determine if 

a certain part number is installed on the 

left-hand and right-hand MLG retraction 

actuator, and if necessary, a general 

visual inspection for discrepancies 

(such as cracks, damage, and movement) 

between the actuator rod end and shock 

strut lug of the MLG retraction actuator. 

The corrective actions include: If any 

discrepancy is found during any 

inspection, including any movement 

between the actuator rod-end and shock 

strut lug, replace the MLG retraction 

actuator, and as applicable, replace the 

anti-rotation pin and the attachment 

bolt with a new pin and bolt; replace the 

actuator with a new actuator having a 

certain part number, and modify the 

attachment points. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Use Additional Service 

Bulletins 

EMBRAER requested that we revise 

the NPRM (76 FR 72855, November 28, 

2011) to include EMBRAER Service 

Bulletin 190LIN–32–0014, dated 

February 10, 2011 (for Model 190–100 

ECJ airplanes); and EMBRAER Service 

Bulletin 190LIN–32–0015, dated 

February 10, 2011 (for Model 190–100 

ECJ airplanes); as additional service 

information for the inspection and 

replacement of the MLG retraction 

actuator, bolt, and anti-rotation pin. 

We agree with EMBRAER’s request to 

add additional service information to 

this AD. EMBRAER Service Bulletin 

190LIN–32–0014, dated February 10, 

2011 (for Model 190–100 ECJ airplanes), 

provides procedures for doing the 

inspection; and EMBRAER Service 

Bulletin 190LIN–32–0015, dated 

February 10, 2011 (for Model 190–100 

ECJ airplanes, provides procedures for 

the replacement. The procedures to do 

the inspection and replacement are 

essentially the same as those specified 

in EMBRAER Service Bulletin 190–32– 

0036, dated October 4, 2010 (for Model 

ERJ 190 airplanes); and EMBRAER 

Service Bulletin 190–32–0037, dated 

October 6, 2010 (for Model ERJ 190 

airplanes). We have revised this AD 

accordingly. 

Request To Allow Flight After Damage 

Is Found 

EMBRAER requested that we revise 

the NPRM (76 FR 72855, November 28, 

2011) to allow further flight within 500 

flight cycles after any damage is found 

on the airplane. EMBRAER stated that 

EMBRAER Service Bulletin 190LIN–32– 

0014, dated February 10, 2011 (for 

Model 190–100 ECJ airplanes); 

EMBRAER Service Bulletin 190LIN–32– 

0015, dated February 10, 2011 (for 

Model 190–100 ECJ airplanes); and 

Brazilian Airworthiness Directive 2011– 

02–01, dated February 12, 2011; allows 

replacement of the MLG retraction 

actuator, the attachment bolt, and the 

anti-rotation pin within the next 500 

flight cycles if any discrepancy is found. 

EMBRAER stated that the NPRM 

requires that any discrepancy found be 

replaced before further flight. 

We disagree with EMBRAER’s request 

to allow further flight within 500 flight 

cycles after any damage is found on the 

airplane. Our policy requires repair of 

known cracks or damage before further 

flight (though we might make 


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