This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

6685 

Vol. 77, No. 27 

Thursday, February 9, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0108; Directorate 

Identifier 2011–NM–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 767 airplanes. The 

existing AD currently requires an 

inspection to detect cracks and fractures 

of the outboard hinge fitting assemblies 

on the trailing edge of the inboard main 

flap, and follow-on and corrective 

actions if necessary. For certain 

airplanes, the existing AD also requires 

a one-time inspection to determine if a 

tool runout option has been performed 

in the area. Since we issued that AD, we 

have received reports of hinge assembly 

fractures found before the currentlyrequired inspection cycle compliance 

times on certain airplanes. This 

proposed AD reduces compliance times 

for Model 767–400ER series airplanes. 

In addition, this proposed AD would 

revise the applicability to include an 

additional airplane. We are proposing 

this AD to prevent the inboard aft flap 

from separating from the wing and 

potentially striking the airplane, which 

could result in damage to the 

surrounding structure and potential 

personal injury. 

DATES: We must receive comments on 

this proposed AD by March 26, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

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; 

telephone 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, 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0108; Directorate Identifier 

2011–NM–049–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 16, 2003, we issued AD 

2003–13–01, Amendment 39–13201 (68 

FR 37402, June 24, 2003), for certain 

Model 767 airplanes. That AD requires 

an inspection to detect cracks and 

fractures of the outboard hinge fitting 

assemblies on the trailing edge of the 

inboard main flap, and follow-on and 

corrective actions if necessary. For 

certain airplanes, that AD also requires 

a one-time inspection to determine if a 

tool runout option has been performed 

in the area. That AD resulted from a 

report indicating that, during a routine 

maintenance inspection, fractured lugs 

were found on both hinge fittings of the 

outboard hinge assembly mounted to 

the inboard main flap on a Boeing 

Model 767–300 series airplane. We 

issued that AD to prevent the inboard 

aft flap from separating from the wing 

and potentially striking the airplane, 

which could result in damage to the 

surrounding structure and potential 

personal injury. 

Actions Since Existing AD Was Issued 

Since we issued AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, 

June 24, 2003), we have determined 

that, due to hinge assembly fractures 

found before the currently-required 

inspection cycle compliance times on 

certain airplanes affected by that AD, 

compliance times need to be reduced for 

the initial and repetitive inspections for 

Model 767–400ER series airplanes. 

In addition, we have determined that 

the airplane having line number 877 

was inadvertently omitted from the 

applicability of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, 

June 24, 2003). 

Relevant Service Information 

AD 2003–13–01, Amendment 39– 

13201 (68 FR 37402, June 24, 2003), 

referred to Boeing Alert Service Bulletin 

767–57A0079, dated June 20, 2002, as 

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6686 Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules 

the appropriate source of service 

information for inspections and 

terminating actions for Model 767– 

400ER series airplanes. Boeing has since 

revised this service bulletin. We 

reviewed Boeing Alert Service Bulletin 

767–57A0079, Revision 1, dated May 6, 

2010. This service bulletin reduces the 

initial compliance time and repetitive 

intervals for inspections of the outboard 

hinge fitting assemblies on the trailing 

edge of the inboard main flap for Model 

767–400ER series airplanes. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain 

certain requirements of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, 

June 24, 2003). This proposed AD 

would reduce the compliance times for 

Model 767–400ER series airplanes. In 

addition, this proposed AD would 

revise the applicability to include an 

additional airplane. 

Changes to Existing AD 

This proposed AD would retain 

certain requirements of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, 

June 24, 2003). Since AD 2003–13–01 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2003–13–01 Amendment 39-13201 (68 FR 

37402, June 24, 2003) 

Corresponding 

requirement in this 

proposed AD 

paragraph (a) paragraph (g) 

paragraph (b) paragraph (h) 

paragraph (c) paragraph (i)(1) 

paragraph (d) paragraph (i)(2) 

paragraph (f) paragraph (j) 

paragraph (g) paragraph (l) 

paragraph (h) paragraph (k) 

Because there is no longer a need for 

inspection results, this proposed AD 

would also remove the reporting 

requirement from AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, 

June 24, 2003). 

Costs of Compliance 

We estimate that this proposed AD 

affects 38 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Detailed inspection [retained from AD 

2003–13–01, Amendment 39–13201 

(68 FR 37402, June 24, 2003)].

2 work-hours × $85 per hour = $170 per 

inspection cycle.

$0 $170 per inspection 

cycle.

$6,460 per inspection cycle. 

Detailed and eddy current inspections 

[retained from AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, 

June 24, 2003)].

5 work hours × $85 per hour = $425 per 

inspection cycle.

0 $425 per inspection 

cycle.

$16,150 per inspection cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed 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 

Replacement [retained from AD 2003–13–01, Amendment 39–13201 (68 FR 37402, June 24, 2003)].24 work hours × $85 per hour = $2,040 .......................... $45,400 $47,440 

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 have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(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. 

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Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules 6687 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing airworthiness directive (AD) 

2003–13–01, Amendment 39–13201 (68 

FR 37402, June 24, 2003), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2012–0108; Directorate Identifier 2011– 

NM–049–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by March 26, 2012. 

(b) Affected ADs 

This AD supersedes AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003). 

(c) Applicability 

The Boeing Company Model 767–200, 

–300, and –300F series airplanes, as specified 

in Boeing Service Bulletin 767–57A0076, 

Revision 1, dated March 29, 2001; and Model 

767–400ER series airplanes, as specified in 

Boeing Alert Service Bulletin 767–57A0079, 

Revision 1, dated May 6, 2010; certificated in 

any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of hinge 

assembly fractures found before the 

currently-required inspection cycle 

compliance times on certain airplanes. We 

are issuing this AD to prevent the inboard aft 

flap from separating from the wing and 

potentially striking the airplane, which could 

result in damage to the surrounding structure 

and potential personal injury. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

Restatement of Certain Requirements of AD 

2003–13–01, Amendment 39–13201 (68 FR 

37402, June 24, 2003), With Revised Service 

Information 

(g) Inspection 

Perform either a detailed inspection, or a 

detailed inspection plus an eddy current 

inspection, of the outboard hinge fitting 

assemblies on the trailing edge of the inboard 

main flap to detect cracks and fractures and 

evidence of a tool runout option, as 

applicable. For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’ 

(1) For Model 767–200, –300, and –300F 

series airplanes identified in Boeing Service 

Bulletin 767–57A0076, Revision 1, dated 

March 29, 2001: Inspect before the airplane 

accumulates 2,700 total flight cycles, or 

within 90 days after July 29, 2003 (the 

effective date of AD 2003–13–01, 

Amendment 39–13201 (68 FR 37402, June 

24, 2003)), whichever occurs later, in 

accordance with Boeing Service Bulletin 

767–57A0076, Revision 1, dated March 29, 

2001. 

(2) For Model 767–400ER series airplanes 

identified in Boeing Alert Service Bulletin 

767–57A0079, dated June 20, 2002: Inspect 

before the airplane accumulates 12,000 total 

flight cycles, except as required by paragraph 

(m) of this AD, in accordance with Boeing 

Alert Service Bulletin 767–57A0079, dated 

June 20, 2002; or Revision 1, dated May 6, 

2010. As of the effective date of this AD, only 

Revision 1 may be used. 

(h) Follow-on/Corrective Actions 

Following the initial inspections required 

by paragraph (g) of this AD: Perform 

applicable follow-on and corrective actions at 

the times specified in Figure 1 of Boeing 

Service Bulletin 767–57A0076, Revision 1, 

dated March 29, 2001 (for Model 767–200, 

–300, and –300F series airplanes); or Boeing 

Alert Service Bulletin 767–57A0079, dated 

June 20, 2002, or Boeing Alert Service 

Bulletin 767–57A0079, Revision 1, dated 

May 6, 2010 (for Model 767–400ER series 

airplanes); until the inspection required by 

paragraph (n) of this AD is accomplished. 

After the effective date of this AD, only 

Boeing Alert Service Bulletin 767–57A0079, 

Revision 1, dated May 6, 2010, may be used 

for Model 767–400ER series airplanes. Do the 

follow-on and corrective actions (including 

repetitive inspections and replacement of the 

fittings with new fittings), in accordance with 

Part 1 or Part 2 of Boeing Service Bulletin 

767–57A0076, Revision 1, dated March 29, 

2001 (for Model 767–200, –300, and –300F 

series airplanes); or Boeing Alert Service 

Bulletin 767–57A0079, dated June 20, 2002, 

or Boeing Alert Service Bulletin 767– 

57A0079, Revision 1, dated May 6, 2010 (for 

Model 767–400ER series airplanes); except as 

required by paragraph (i)(2) of this AD. After 

the effective date of this AD, only Boeing 

Alert Service Bulletin 767–57A0079, 

Revision 1, dated May 6, 2010, may be used 

for Model 767–400ER series airplanes. For 

Model 767–200, –300, and –300F series 

airplanes: If the fitting has the tool runout, 

and no cracking or fracture is found during 

the inspection, this AD requires no further 

action for that hinge fitting. 

(i) Exceptions to Service Bulletin Procedures 

For this AD, the following exceptions 

apply: 

(1) Where the terminating action in Part 3 

of Boeing Service Bulletin 767–57A0076, 

Revision 1, dated March 29, 2001; and 

Boeing Alert Service Bulletin 767–57A0079, 

dated June 20, 2002, and Revision 1, dated 

May 6, 2010; is specified as corrective action: 

This AD requires that the terminating action, 

if required, be accomplished before further 

flight. 

(2) Boeing Service Bulletin 767–57A0076, 

Revision 1, dated March 29, 2001, specifies 

to contact Boeing before the terminating 

action is done as corrective action for any 

cracking or fracture found on a Model 767– 

200, –300, or –300F series airplane with the 

tool runout. This AD requires that any such 

crack or fracture on those airplanes be 

repaired in accordance with Part 3 of Boeing 

Service Bulletin 767–57A0076, Revision 1, 

dated March 29, 2001. This AD does not 

require a report. 

(j) Optional Terminating Action 

Unless required to do so by paragraph (h) 

of this AD: Operators may choose to 

accomplish the terminating action (including 

replacement of the fittings with new fittings, 

and reinstallation of existing upper skin 

access panels and fairing midsections on the 

trailing edge of the main flap) in accordance 

with Part 3 of the Work Instructions of 

Boeing Service Bulletin 767–57A0076, 

Revision 1, dated March 29, 2001; or Boeing 

Alert Service Bulletin 767–57A0079, dated 

June 20, 2002, or Boeing Alert Service 

Bulletin 767–57A0079, Revision 1, dated 

May 6, 2010; as applicable. After the effective 

date of this AD, only Boeing Alert Service 

Bulletin 767–57A0079, Revision 1, dated 

May 6, 2010, may be used for Model 767– 

400ER series airplanes. Accomplishment of 

the terminating action terminates the 

repetitive inspection requirements of 

paragraph (h) of this AD. 

(k) Part Installation 

As of July 29, 2003, no person may install 

on any airplane identified in Boeing Service 

Bulletin 767–57A0076, dated October 26, 

2000; and Boeing Alert Service Bulletin 767– 

57A0079, dated June 20, 2002; a hinge fitting 

assembly that has any part number listed in 

table 1 of this AD, unless the applicable 

requirements of this AD have been 

accomplished for that fitting. As of the 

effective date of this AD, no person may 

install on any airplane identified in 

paragraph (c) of this AD, a hinge fitting 

assembly that has any part number listed in 

table 1 of this AD, unless the applicable 

requirements of this AD have been 

accomplished for that fitting. 

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6688 Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules 

TABLE 1—HINGE FITTING ASSEMBLY

PART NUMBERS

113T2271–13 113T2271–14 

113T2271–23 113T2271–24 

113T2271–29 113T2271–30 

113T2271–33 113T2271–34 

113T2271–401 113T2271–402 

(l) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Actions done before July 29, 2003, in 

accordance with Boeing Alert Service 

Bulletin 767–57A0076, dated October 26, 

2000, are acceptable for compliance with the 

corresponding requirements of paragraphs 

(g), (h), (j), and (k) of this AD. 

New Requirements of This AD 

(m) Initial Inspection 

For Model 767–400ER airplanes identified 

in Boeing Alert Service Bulletin 767– 

57A0079, Revision 1, dated May 6, 2010, on 

which the inspection required in paragraph 

(g) of this AD has not been done as of the 

effective date of this AD: Before the 

accumulation of 6,000 total flight cycles, or 

within 750 flight cycles after the effective 

date of this AD, whichever occurs later, 

perform either a detailed inspection or a 

detailed inspection plus an eddy current 

inspection to detect cracks or fractures of the 

outboard hinge fitting assemblies on the 

trailing edge of the inboard main flap, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–57A0079, Revision 1, dated May 6, 2010. 

Accomplishment of this inspection 

terminates the inspection requirement of 

paragraph (g)(2) of this AD. 

(n) Repetitive Inspections 

For Model 767–400ER airplanes: Repeat 

either inspection specified in paragraph (h) 

or (m) of this AD, as applicable, at the time 

specified in paragraph (n)(1) or (n)(2) of this 

AD, as applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–57A0079, Revision 1, 

dated May 6, 2010. 

(1) If the most recent inspection was a 

detailed inspection, repeat at intervals not to 

exceed 300 flight cycles after doing the 

detailed inspection. 

(2) If the most recent inspections were a 

detailed inspection and an eddy current 

inspection, repeat at intervals not to exceed 

750 flight cycles after doing the detailed 

inspection and eddy current inspection. 

(o) Optional Terminating Action 

For Model 767–400ER airplanes: Replacing 

the fittings with new fittings, in accordance 

with Part 3 of the Work Instructions of 

Boeing Alert Service Bulletin 767–57A0079, 

dated June 20, 2002; or Revision 1, dated 

May 6, 2010; terminates the repetitive 

inspections required by paragraphs (h) and 

(n) of this AD. 

(p) Credit for Actions Accomplished in 

Accordance with Previous Service 

Information 

Actions done before the effective date of 

this AD in accordance with Part 3 of the 

Work Instructions of Boeing Alert Service 

Bulletin 767–57A0079, dated June 20, 2002, 

are acceptable for compliance with the 

requirements of paragraph (h) and (n) of this 

AD. 

(q) 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. 

(r) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: berhane.alazar@faa.gov. 

(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; telephone 

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, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on January 

27, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–2976 Filed 2–8–12; 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] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Bombardier Inc. 

Model CL–215–1A10 and CL–215–6B11 

(CL–215T Variant) airplanes. The 

existing 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. 

Since we issued that AD, we have 

received reports of cracking found 

outside the inspection area. This 

proposed AD would extend the 

inspection area of the rear spar lower 

cap from WS 51.00 to WS 49.50 and 

modify the ultrasonic inspection 

calibration procedure. We are proposing 

this AD to detect and correct cracking of 

the lower caps of the wing front spar 

and rear spar, and lower wing skin, 

which could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 26, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

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