Federal Register / Vol. 77, No. 107 / Monday, June 4, 2012 / Rules and Regulations 32889 

plate, which could cause the vertical 

stabilizer nose plate to fail and result in loss 

of control of the sailplane. 

(f) Actions and Compliance 

Unless already done, do the following 

actions: 

(1) Within 3 months after July 9, 2012 (the 

effective date of this AD): 

(i) Inspect, from the top, the front and rear 

side of the nose plate, part number (P/N) 

109–2160.01, in the vertical stabilizer for 

corrosion and flaking following Part A of the 

Accomplishment Instructions in Grob 

Aircraft Service Bulletin No. MSB817–58, 

dated November 24, 2011. Repetitively 

thereafter inspect at intervals not to exceed 

12 months. 

(ii) Install an access panel on the left side 

of the vertical stabilizer following Grob 

Aircraft Repair Instruction Doc. No. RI 817– 

010/1, issue date December 20, 2011, as 

specified in Grob Aircraft Service Bulletin 

No. MSB 817–060, dated November 24, 2011. 

(iii) Through the access panel installed as 

required in paragraph (f)(1)(ii) of this AD, 

inspect, from below, the nose plate, P/N 109– 

2160.01, for corrosion and flaking following 

Part B of the Accomplishment Instructions in 

Grob Aircraft Service Bulletin No. MSB817– 

58, dated November 24, 2011. Repetitively 

thereafter inspect at intervals not to exceed 

12 months. 

(2) If any corrosion or flaking is found on 

the nose plate, P/N 109–2160.01, during any 

inspection required in paragraphs (f)(1)(i) or 

(f)(1)(iii) of this AD, replace P/N 109–2160.01 

with a serviceable part. Do the replacement 

following Grob Aircraft Repair Instruction 

Doc. No. RI 817–009, issue date November 

17, 2011, as specified in Grob Aircraft 

Service Bulletin No. MSB817–58, dated 

November 24, 2011. After replacement, 

continue with the repetitive inspections 

required in paragraphs (f)(1)(i) and (f)(1)(iii) 

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: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any sailplane 

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 European Aviation Safety 

Agency (EASA) AD No. 2012–0027, dated 

February 14, 2012; Grob Aircraft Service 

Bulletin No. MSB817–58 and Grob Aircraft 

Service Bulletin No. MSB 817–060, both 

dated November 24, 2011; Grob Aircraft 

Repair Instruction Doc. No. RI 817–009, issue 

date November 17, 2011; and Grob Aircraft 

Repair Instruction Doc. No. RI 817–010/1, 

issue date December 20, 2011, for related 

information. 

(i) 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) under 5 

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

following service information on July 9, 

2012: 

(i) Grob Aircraft Service Bulletin No. 

MSB817–58, dated November 24, 2011; 

(ii) Grob Aircraft Service Bulletin No. MSB 

817–060, dated November 24, 2011; 

(iii) Grob Aircraft Repair Instruction Doc. 

No. RI 817–009, issue date November 17, 

2011; and 

(iv) Grob Aircraft Repair Instruction Doc. 

No. RI 817–010/1, issue date December 20, 

2011. 

(2) For service information identified in 

this AD, contact Grob Aircraft AG, 

Lettenbachstrasse 9, D–86874 TussenhausenMattsies, Germany; telephone: +49 (0) 8268 

998139; fax: +49 (0) 8268 998200; email: 

productsupport@grob-aircraft.com; Internet 

http://www.grob-aircraft.eu/. 

(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 

16, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–12409 Filed 6–1–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1320; Directorate 

Identifier 2011–NM–208–AD; Amendment 

39–17066; AD 2012–11–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 777 airplanes. 

This AD was prompted by four reports 

of retaining cross bolt hardware not 

fully engaged into the fuse pins of the 

forward trunnion lower housing of the 

main landing gear (MLG), which could 

result in an incorrect MLG emergency 

landing break-away sequence. This AD 

requires a detailed inspection of the fuse 

pin cross bolts and fuse pins of the left 

and right MLG forward trunnion lower 

housing to verify that the cross bolts are 

correctly installed and that there are no 

missing fuse pins, and replacement of 

the fuse pins if necessary. We are 

issuing this AD to prevent an incorrect 

emergency landing MLG break-away 

sequence, which could result in 

puncturing of the wing box and 

consequent fuel leaks and an airplane 

fire. Failure of the fuse pins could also 

result in a possible landing gear collapse 

causing a runway excursion during takeoff or landing. 

DATES: This AD is effective July 9, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 9, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; phone: 206–544–5000, extension 

1; fax: 206–766–5680; email: 

me.boecom@boeing.com; Internet: 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 


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32890 Federal Register / Vol. 77, No. 107 / Monday, June 4, 2012 / Rules and Regulations 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

James Sutherland, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6533; fax: 425–917–6590; email: 

James.Sutherland@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 published in the Federal 

Register on December 15, 2011 (76 FR 

77937). That NPRM proposed to require 

a detailed inspection of the fuse pin 

cross bolts and fuse pins of the forward 

trunnion lower housing of the left and 

right MLG to verify that the cross bolts 

are correctly installed and that there are 

no missing fuse pins, and replacing all 

fuse pins in the MLG forward trunnion 

upper and lower housing with new fuse 

pins if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 77937, 

December 15, 2011) and the FAA’s 

response to each comment. 

Support for the NPRM (76 FR 77937, 

December 15, 2011) 

United Airlines stated it concurs with 

the proposed rule (76 FR 77937, 

December 15, 2011) to inspect for the 

correct installation of the cross bolts and 

the fuse pins to ensure a high level of 

safety for the 777 fleet. 

Thomas Hayden Barnes stated that he 

supports efforts to ensure airline safety 

and the proposed rule (76 FR 77937, 

December 15, 2011). 

Request To Clarify Fuse Pin 

Replacement 

American Airlines (American) and 

FedEx requested clarification as to 

whether the NPRM (76 FR 77937, 

December 15, 2011) requires changing 

all fuse pins on both left and right MLG 

even if the discrepant condition is only 

found on one side of the airplane MLG. 

We agree to clarify the fuse pin 

replacement by changing paragraph (g) 

of the final rule to read, in part: ‘‘If any 

cross bolt of the MLG forward trunnion 

lower housing is not installed correctly, 

or if any fuse pin of the MLG forward 

trunnion lower housing is missing: 

Before further flight, replace all fuse 

pins in the MLG forward trunnion 

upper and lower housing on the side, or 

sides of the airplane, where the missing 

or incorrectly installed fuse pin/pins 

were discovered * * *.’’ 

Request To Use Maintenance Pits and 

Clarify Procedure 

American requested that the NPRM 

(76 FR 77937, December 15, 2011) 

permit the use of maintenance pits in 

lieu of jacking the airplane, as specified 

in Boeing Alert Service Bulletin 777– 

57A0090, dated August 24, 2011. 

American stated that it is acceptable to 

stabilize the airplane on jacks and lower 

maintenance pits until the wheels do 

not touch the surface, and accomplishes 

the same effect of unloading the 

airplane weight from the trunnion for 

the purposes of changing the fuse pins. 

American also noted that the phrase 

‘‘until the wheels are just off the 

ground’’ in Part 2 of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 777–57A0090, 

dated August 24, 2011, might be 

construed to be a dimension without 

tolerance. 

We agree that the use of lowered 

maintenance pits to unload the MLG 

does have the same effect as lifting. We 

also agree that the meaning of the 

phrase ‘‘just off the ground’’ is a 

dimension without tolerance. We have 

changed paragraph (g) of the final rule 

to specify that step 1 in Part 2 of 

paragraph 3.B. of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 777–57A0090, dated August 24, 

2011, is not considered regulatory for 

the purposes of this AD. 

Request To Change Applicability 

Boeing and FedEx requested that the 

applicability of the NPRM (76 FR 77937, 

December 15, 2011) list only the 

airplanes specified in Boeing Alert 

Service Bulletin 777–57A0090, dated 

August 24, 2011. Boeing stated that 

airplanes not listed in this service 

information have been inspected during 

production to ensure they do not have 

the unsafe condition. FedEx stated that 

it currently flies 6 aircraft that are not 

listed in the NPRM, and is adding new 

aircraft to its fleet, none of which will 

be listed in the NPRM. 

We agree. The intent of the AD is to 

ensure that inspections are done on 

airplanes on which Boeing was unable 

to confirm that the cross bolts are 

installed correctly and on which there 

are no missing fuse pins. We have 

changed paragraph (c) of the final rule 

to apply to the airplanes identified in 

Boeing Alert Service Bulletin 777– 

57A0090, dated August 24, 2011. 

Additional Change Made to This Final 

Rule 

We have removed Note 1 that 

followed paragraph (g) in the NPRM (76 

FR 77937, December 15, 2011) from the 

final rule. That information is contained 

in Note 7 of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 777–57A0090, dated August 24, 

2011, and does not need to be included 

in the AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

77937, December 15, 2011) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 77937, 

December 15, 2011). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 166 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 77, No. 107 / Monday, June 4, 2012 / Rules and Regulations 32891 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Detailed Inspection ............................................. 3 work-hours × $85 per hour = $255 ................. $0 $255 $42,330 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replace fuse pins .......................... 44 work-hours × $85 per hour = 

$3,740.

Between $15,216 and $52,620 .... Between $18,956 and $56,360. 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–11–03 The Boeing Company: 

Amendment 39–17066; Docket No. 

FAA–2011–1320; Directorate Identifier 

2011–NM–208–AD. 

(a) Effective Date 

This AD is effective July 9, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 777–57A0090, dated August 

24, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by four reports of 

retaining cross bolt hardware not fully 

engaged into the fuse pins of the forward 

trunnion lower housing of the main landing 

gear (MLG), which could result in an 

incorrect MLG emergency landing breakaway sequence. We are issuing this AD to 

prevent an incorrect emergency landing MLG 

break-away sequence, which could result in 

puncturing of the wing box and consequent 

fuel leaks and an airplane fire. Failure of the 

fuse pins could also result in a possible 

landing gear collapse causing a runway 

excursion during take-off or landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Detailed Inspection and Replacement 

Within 1,125 days after the effective date 

of this AD, perform a detailed inspection of 

the fuse pin cross bolts and fuse pins of the 

left and right MLG forward trunnion lower 

housing to verify that the cross bolts are 

installed correctly and that there are no 

missing fuse pins, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–57A0090, dated August 

24, 2011. If any cross bolt of the MLG 

forward trunnion lower housing is not 

installed correctly, or if any fuse pin of the 

MLG forward trunnion lower housing is 

missing: Before further flight, replace all fuse 

pins in the MLG forward trunnion upper and 

lower housing on the side, or sides, of the 

airplane where the missing or incorrectly 

installed fuse pin/pins were discovered, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–57A0090, dated August 24, 2011, except 

step 1 in Part 2 of paragraph 3.B of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–57A0090, dated August 

24, 2011, is not considered regulatory for the 

purposes of this AD. 


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32892 Federal Register / Vol. 77, No. 107 / Monday, June 4, 2012 / Rules and Regulations 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(i) Related Information 

For more information about this AD, 

contact James Sutherland, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6533; fax: 425–917–6590; email: 

James.Sutherland@faa.gov. 

(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 51: 

(i) Boeing Alert Service Bulletin 777– 

57A0090, dated August 24, 2011. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680; email: me.boecom@boeing.com; 

Internet: https://www.myboeingfleet.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(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 NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on May 18, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–12910 Filed 6–1–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0109; Directorate 

Identifier 2010–NM–244–AD; Amendment 

39–17067; AD 2012–11–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Bombardier Inc. Model CL–215– 

1A10 and CL–215–6B11 (CL–215T 

Variant) airplanes. That AD currently 

requires repetitive inspections to detect 

cracking of the lower cap of the wing 

front and rear spars at wing station (WS) 

51.00, and the wing lower skin. 

Additional actions, if cracking is found, 

include reworking the lower cap of the 

front or rear spar, inspecting for 

cracking, and repairing any cracking. 

The existing AD also requires reporting 

inspection results. This new AD 

requires extending the inspection area 

of the rear spar lower cap from WS 

51.00 to WS 49.50 and modifying the 

ultrasonic inspection calibration 

procedure. This AD was prompted by 

reports of cracking found outside the 

inspection area. We are issuing this AD 

to detect and correct cracking of the 

lower caps of the wing front and rear 

spars, and lower wing skin, which could 

result in reduced structural integrity of 

the airplane. 

DATES: This AD becomes effective July 

9, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 9, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of October 6, 2005 (70 FR 

52009, September 1, 2005). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 4, 1998 (63 FR 

7640, February 17, 1998). 

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: 

George Duckett, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Westbury, New York 

11590; telephone (516) 228–7325; fax 

(516) 794–5531. 

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 February 9, 2012 (77 FR 

6688), and proposed to supersede AD 

2005–18–05, Amendment 39–14245 (70 

FR 52009, September 1, 2005). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Cracks have been found in the rear spar of 

the left wing at Wing Station (WS) 51.00 on 

several aircraft in service. On some aircraft, 

the cracks propagated through the lower spar 

cap and fail-safe straps into the spar web and 

the lower wing skin. The cracks are not 

visible from outside the aircraft. 

Revision 2 of this [Transport Canada Civil 

Aviation] AD is issued as a result of cracks 

found outside the inspection area specified 

in Revision 1. This revision extends the 

inspection area of the rear spar lower cap 

from WS 51.00 to WS 49.50 and to modify 

the ultrasonic inspection calibration 

procedure. 

Cracking of the lower caps of the wing 

front and rear spars, and lower wing 

skin, could result in reduced structural 

integrity of the airplane. You may obtain 

further information by examining the 

MCAI in the AD docket. 

AD 2005–18–05, Amendment 39– 

14245 (70 FR 52009, September 1, 

2005), specifies Model CL–215–6B11 

(CL–415 Variant) airplanes in the 

applicability, but also specifies serial 

numbers 1001 though 1125. The serial 

numbers for Model CL–215–6B11 (CL– 

415 Variant) airplanes start at 2001. We 

have determined that Model CL–215– 

6B11 (CL–415 Variant) airplanes are not 

subject to the identified unsafe 

condition. Therefore, we have removed 

Model CL–215–6B11 (CL–415 Variant) 

airplanes from the applicability of this 

AD. 


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