Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36125 

Furthermore, 14 CFR regulations and 

current system safety assessment policy 

and techniques do not address potential 

security vulnerabilities, which could be 

exploited by unauthorized access to 

airplane systems, data buses, and 

servers. Therefore, these special 

conditions are issued to ensure that the 

security (i.e., confidentiality, integrity, 

and availability) of airplane systems is 

not compromised by unauthorized 

wired or wireless electronic 

connections. 

Applicability 

As discussed above, these special 

conditions are applicable to the Model 

G280. Should GALP apply at a later date 

for a change to the type certificate to 

include another model incorporating the 

same novel or unusual design feature, 

the special conditions would apply to 

that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of airplane. It is not a rule of general 

applicability. 

The substance of these special 

conditions has been subjected to the 

notice and comment period in several 

prior instances and has been derived 

without substantive change from those 

previously issued. It is unlikely that 

prior public comment would result in a 

significant change from the substance 

contained herein. Therefore, because a 

delay would significantly affect the 

certification of the airplane, which is 

imminent, the FAA has determined that 

prior public notice and comment are 

unnecessary and impracticable, and 

good cause exists for adopting these 

special conditions upon issuance. The 

FAA is requesting comments to allow 

interested persons to submit views that 

may not have been submitted in 

response to the prior opportunities for 

comment described above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

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 Gulfstream 

Aerospace LP, Model Gulfstream G280 

airplanes. 

1. Airplane Electronic System 

Security Protection from Unauthorized 

External Access. The applicant must 

ensure airplane electronic system 

security protection from access to or by 

unauthorized sources external to the 

airplane, including those possibly 

caused by maintenance activity. 

2. The applicant must ensure that 

electronic system security threats are 

identified and assessed, and that 

effective electronic system security 

protection strategies are implemented to 

protect the airplane from all adverse 

impacts on safety, functionality, and 

continued airworthiness. 

3. The applicant must establish 

appropriate procedures to allow the 

operator to ensure that continued 

airworthiness of the aircraft is 

maintained, including all post type 

certification modifications that may 

have an impact on the approved 

electronic system security safeguards. 

Issued in Renton, Washington, on June 7, 

2012. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14787 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0250; Directorate 

Identifier 2011–CE–043–AD; Amendment 

39–17063; AD 2012–10–14] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

SOCATA Model TBM 700 airplanes. 

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 installation of 

an incorrect part number during 

overhaul of the nose landing gear. We 

are issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective July 23, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 23, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov 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 SOCATA—Direction 

des Services, 65921 Tarbes Cedex 9, 

France; telephone: +33 (0)5 62 41 73 00; 

fax: +33 (0)5 62 41 76 54; or in the 

United States contact SOCATA North 

America, Inc., North Perry Airport, 7501 

South Airport Road, Pembroke Pines, 

Florida 33023; telephone: (954) 893– 

1400; fax: (954) 964–4141; email: 

mysocata@socata.daher.com; Internet: 

www.socatanorthamerica.com. You may 

review copies of the 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. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090; email: 

albert.mercado@faa.gov. 

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 March 9, 2012 (77 FR 

14314). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A TBM 700 operator reported a case of 

rupture of the bolt attaching the actuator 

hinge axle on the NLG of the aeroplane. The 

results of the technical investigations carried 

out by SOCATA revealed that this rupture 

could have been caused by the installation of 

a bolt bearing incorrect Part Number (P/N) 

during overhaul of the NLG. Furthermore, the 

investigations led to identify the NLG part 

numbers identified by S/N which are 

potentially affected after repair or overhaul. 

This condition, if not detected and 

corrected, could lead to partial 

disengagement of the actuator hinge axle on 

the NLG of the aeroplane, resulting in nose 

landing gear collapse, possibly resulting in 

structural damage to the aeroplane. 

To address this condition, SOCATA have 

developed Service Bulletin SB 70–194–32 

which gives instructions for accomplishing 

repetitive checks of the bolt attaching 

actuator hinge axle on NLG and for replacing 


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36126 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 

the bolt attaching the actuator hinge axle 

with a correct bolt P/N. 

For the reasons described above, this AD 

requires accomplishment of repetitive checks 

of potentially affected NLGs and replacement 

of the bolt attaching the actuator hinge axle 

with a serviceable bolt. This AD also 

prohibits installation on any aeroplane of a 

potentially affected NLG, unless the bolt 

attaching the actuator hinge axle has been 

replaced with a serviceable bolt and the NLG 

has been marked with a green varnish line. 

Following issuance of EASA AD 2011– 

0225–E, it has been determined that further 

NLG P/Ns and S/Ns are affected by this AD. 

SOCATA have developed an erratum to SB 

70–194–32 amendment 2, which lists the 

new P/Ns and S/Ns as well affected by this 

AD. 

For the above reason, this AD, which 

supersedes EASA AD 2011–0225–E, retaining 

its requirements, extends the list of NLG 

P/Ns and S/Ns affected by the AD 

requirements. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM 

(77 FR 14314, March 9, 2012) 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 (77 FR 

14314, March 9, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 14314, 

March 9, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

448 products of U.S. registry. We also 

estimate that it would take about 

1 work-hour per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $35 per 

product. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $53,760, or $120 per product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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; 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: 

2012–10–14 SOCATA: Amendment 39– 

17063; Docket No. FAA–2012–0250; 

Directorate Identifier 2011–CE–043–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective July 23, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to SOCATA Model TBM 

700 airplanes, all serial numbers (S/N), 

certificated in any category, equipped with 

one of the following landing gears: 

(1) Part number (P/N) D23766000 or 

D23766000–X, serial numbers (S/N) B001 

through B373; B375; AR1000 through 

AR1023; AR1025 through AR1031; AR1033 

through AR1036; AAB00000A through 

AAB13766Z; AAB00000 through AAB13766; 

and EURXXX; or 

(2) P/N 21130–001–XY or 21130–000–XY, 

all S/N. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

(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 installation 

of an incorrect part number during overhaul 

of the nose landing gear. We are issuing this 

AD to detect and correct installation of 

incorrect P/N NLG bolts, which if not 

corrected could result in NLG collapse with 

consequent structural damage to the airplane. 

(f) Actions and Compliance 

Unless already done, do the following 

actions using the Accomplishment 

Instructions of DAHER-SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70– 

194–32, Amendment 2, dated November 

2011, including Erratum, dated December 

2011: 

(1) Although the European Aviation Safety 

Agency (EASA) MCAI allows the inspection 

of the NLG washer to be done by a pilotowner, the U.S. regulatory system requires all 

actions of this AD to be done by a certified 

mechanic. 


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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36127 

(2) Within 5 flight cycles (FC) after July 23, 

2012 (the effective date of this AD), inspect 

the installed NLG to determine if it is one of 

the affected P/Ns and S/Ns as listed in 

paragraph (c) of this AD. 

(i) If FC data is not available, the use of a 

one-to-one FC to flight hour conversion must 

be applied (example: 5 FC equal 5 hours 

time-in-service (TIS)). 

(ii) For the purpose of this AD, when an 

NLG P/N reference is followed by –X or –XY, 

the X or XY can be any numerical digit, and 

when an NLG S/N reference is EURXXX, the 

XXX can be any numerical digit. 

(3) If during the inspection required in 

paragraph (f)(2) of this AD, you determine the 

NLG installed is one of the affected P/Ns and 

S/Ns listed in paragraph (c) of the AD, 

inspect for free rotation the washer of the 

NLG. Repetitively thereafter inspect the 

washer of the NLG for free rotation before 

every flight until the replacement and 

landing gear marking required in paragraphs 

(f)(4)(i) and (f)(4)(ii) or paragraphs (f)(5)(i) 

and (f)(5)(ii) of this AD are done. 

(4) If, during any inspection required by 

paragraph (f)(3) of this AD, the washer of the 

NLG rotates freely, before further flight, do 

the following actions: 

(i) Replace the bolt attaching the actuator 

hinge axle of the NLG with a serviceable bolt 

P/N 5101301111. 

(ii) Mark the landing gear with a green 

varnish line. 

(5) For the NLG P/Ns and S/Ns as listed in 

paragraph (c) of this AD, within 10 months 

after July 23, 2012 (the effective date of this 

AD), unless already done following a 

discrepancy identified during any inspection 

as required by paragraph (f)(3) of this AD, do 

the following actions: 

(i) Replace the bolt attaching the actuator 

hinge axle of the NLG with a serviceable bolt 

P/N 5101301111 and; 

(ii) Mark the landing gear with a green 

varnish line. 

(6) Replacing of the bolt attaching the 

actuator hinge axle of the NLG with a 

serviceable bolt P/N 5101301111 and 

marking the landing gear with a green 

varnish line terminates the repetitive 

inspections required by paragraph (f)(3) of 

this AD. 

(7) After July 23, 2012 (the effective date 

of this AD), do not install an NLG with 

P/N and S/N as listed in paragraph (c) of this 

AD, unless the bolt attaching the actuator 

hinge axle of the NLG has been replaced and 

the NLG has been marked with a green 

varnish line following the requirements 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: Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4119; fax: (816) 329– 

4090; email: albert.mercado@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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(h) Related Information 

Refer to MCAI EASA AD No.: 2011–0235– 

E, dated December 13, 2011; DAHERSOCATA TBM Aircraft Mandatory Service 

Bulletin SB 70–194–32, Amendment 2, dated 

November 2011; and Erratum to DAHERSOCATA TBM Aircraft Mandatory Service 

Bulletin SB 70 194–32, Amendment 2, dated 

December 2011, for related information. 

(i) Material Incorporated by Reference 

(1) You must use DAHER-SOCATA TBM 

Aircraft Mandatory Service Bulletin SB 70– 

194–32, Amendment 2, dated November 

2011, including Erratum, dated December 

2011, 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) under 5 

U.S.C. 552(a) and 1 CFR part 51: 

(2) For service information identified in 

this AD, contact SOCATA—Direction des 

Services, 65921 Tarbes Cedex 9, France; 

telephone: +33 (0)5 62 41 73 00; fax: +33 (0)5 

62 41 7654; or in the United States contact 

SOCATA North America, Inc., North Perry 

Airport, 7501 South Airport Road, Pembroke 

Pines, Florida 33023; telephone: (954) 893– 

1400; fax: (954) 964–4141; email: 

mysocata@socata.daher.com; Internet: 

www.socatanorthamerica.com. 

(3) You may review copies of the 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. 

(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 Kansas City, Missouri, on May 

17, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–12649 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0188; Directorate 

Identifier 2011–NM–120–AD; Amendment 

39–17079; AD 2012–11–15] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all BAE 

SYSTEMS (Operations) Limited Model 

4101 airplanes. This AD was prompted 

by reports of cracking found in the wing 

rear spar. This AD requires a one-time 

detailed inspection for cracks, 

corrosion, and other defects of the rear 

face of the wing rear spar, and repair if 

necessary. We are issuing this AD to 

detect and correct cracking in the rear 

spar, which could propagate to a critical 

length, possibly affecting the structural 

integrity of the area and resulting in a 

fuel tank rupture, with consequent 

damage to the airplane and possible 

injury to its occupants. 

DATES: This AD becomes effective July 

23, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 23, 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: 

Todd Thompson, Aerospace Engineer, 


srobinson on DSK4SPTVN1PROD with RULES