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, 


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36128 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

425–227–1175; 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 March 6, 2012 (77 FR 

13228). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Four cracks were found on a wing rear spar 

by an operator during a fuel leak 

investigation. The cracks were located 

between ribs 6 and 7, immediately inboard of 

the inboard engine rib. The cracks initiated 

at adjacent fastener bores in the rear spar 

upper boom and progressed downwards, 

diagonally, into the rear spar web. 

Such cracking in the rear spar, if not 

detected and corrected, could propagate to a 

critical length, possibly affecting the 

structural integrity of the area and/or 

resulting in a fuel tank rupture, and 

consequent damage to the aeroplane and 

injury to its occupants. 

For the reasons described above, this 

[EASA] AD requires a one-time [detailed] 

inspection [for cracks, corrosion, and other 

defects] of the rear face of the wing rear spar 

and the accomplishment of the associated 

corrective actions [i.e., repair], depending on 

findings. 

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 

received no comments on the NPRM (77 

FR 13228, March 6, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available 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 

13228, March 6, 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 13228, 

March 6, 2012). 

Costs of Compliance 

We estimate that this AD will affect 3 

products of U.S. registry. We also 

estimate that it will take about 25 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

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

be $6,375, or $2,125 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimates for the on-condition actions 

(repairing cracks, corrosion, and defects) 

specified in this AD. 

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 that 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 the NPRM (77 FR 13228, 

March 6, 2012), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations 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: 

2012–11–15 BAE SYSTEMS (Operations) 

Limited: Amendment 39–17079. Docket 

No. FAA–2012–0188; Directorate 

Identifier 2011–NM–120–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective July 23, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to BAE SYSTEMS 

(Operations) Limited Model 4101 airplanes, 

certificated in any category, all models, and 

all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking found in the wing rear spar. 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. 

(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) Detailed Inspection and Repair 

Within 300 flight hours after the effective 

date of this AD, or before further flight if a 


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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36129 

fuel leak is detected in the vicinity of a wing 

rear spar, whichever occurs first: Do a 

detailed inspection for cracks, corrosion, and 

other defects (defects include scratches, 

dents, holes, damage to fastener holes, or 

damage to surface protection and finish) of 

the rear face of the wing rear spars, in 

accordance with the Accomplishment 

Instructions of BAE SYSTEMS (Operations) 

Limited Alert Service Bulletin J41–A57–029, 

dated May 6, 2011. 

(1) If any cracking, corrosion, or other 

defect is found to be within the criteria 

defined in Subject 57–00–00, Wings General, 

of Chapter 57, Wings, of the Jetstream Series 

4100 Structural Repair Manual, Volume 1, 

Revision 30, dated April 15, 2007: Before 

further flight, repair the damage, in 

accordance with the repair instructions 

specified in Subject 57–00–00, Wings 

General, of Chapter 57, Wings, of the 

Jetstream Series 4100 Structural Repair 

Manual, Volume 1, Revision 30, dated April 

15, 2007. 

(2) If any cracking, corrosion, or other 

defect is found exceeding the criteria as 

specified in Subject 57–00–00, Wings 

General, of Chapter 57, Wings, of the 

Jetstream Series 4100 Structural Repair 

Manual, Volume 1, Revision 30, dated April 

15, 2007: Before further flight, repair the 

condition, in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, or EASA (or its delegated 

agent). 

(h) Reporting 

Submit a report of the findings of the 

inspection required by paragraph (g) of this 

AD, including a report of no defects, to BAE 

SYSTEMS (Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone +44 

1292 675207; fax +44 1292 675704; email 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/

RegionalAircraft/index.htm, at the applicable 

time specified in paragraph (h)(1) or (h)(2) of 

this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(i) 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1175; 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. 

(3) Reporting Requirements: 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. 

(j) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0096, dated May 25, 2011, 

and the service information specified in 

paragraphs (j)(1) and (j)(2) of this AD, for 

related information. 

(1) BAE SYSTEMS (Operations) Limited 

Alert Service Bulletin J41–A57–029, dated 

May 6, 2011. 

(2) Subject 57–00–00, Wings General, of 

Chapter 57, Wings, of the Jetstream Series 

4100 Structural Repair Manual, Volume 1, 

Revision 30, dated April 15, 2007. 

(k) 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) BAE SYSTEMS (Operations) Limited 

Alert Service Bulletin J41–A57–029, dated 

May 6, 2011. 

(ii) Subject 57–00–00, Wings General, of 

Chapter 57, Wings, of the Jetstream Series 

4100 Structural Repair Manual, Volume 1, 

Revision 30, dated April 15, 2007. The 

revision level and date of this document are 

identified only in the Record of Revisions 

section of this document. 

(3) For service information identified in 

this AD, contact BAE SYSTEMS (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email RApublications@baesystems.

com; Internet http://www.baesystems.com/

Businesses/RegionalAircraft/index.htm. 

(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 

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 March 

31, 2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13800 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–2012–0293; Directorate 

Identifier 2012–NM–034–AD; Amendment 

39–17081; AD 2012–12–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, Model CL–600–2D15 

(Regional Jet Series 705) airplanes, and 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes. This AD was 

prompted by reports of a bleed air leak 

from the high pressure ducts which was 

not immediately detected by the bleed 

leak detection system. This AD requires 

installing new sensing elements in the 

main landing gear wheel well and the 

overwing area, protective blankets on 

the upper surface of the wing box and 

fuel tubes, and protective shields on the 

rudder quadrant support-beam in the aft 

equipment compartment. We are issuing 

this AD to prevent an undetected bleed 


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