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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Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules 6689 

Que ́bec H4S 1Y9, Canada; phone: 514– 

855–5000; fax: 514–855–7401; email: 

thd.crj@aero.bombardier.com; Internet: 

http://www.bombardier.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 Operations office 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 Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

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, NY 11590; 

telephone (516) 228–7325; fax (516) 

794–5531. 

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–2012–0109; Directorate Identifier 

2010–NM–244–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 based on 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 August 24, 2005, we issued AD 

2005–18–05, Amendment 39–14245 (70 

FR 52009, September 1, 2005). That AD 

required actions intended to address an 

unsafe condition on Bombardier, Inc. 

Model CL–215–1A10, CL–215–6B11 

(CL–215T Variant), and CL–215–6B11 

(CL–415 Variant) airplanes. 

Since we issued AD 2005–18–05, 

Amendment 39–14245 (70 FR 52009, 

September 1, 2005) Transport Canada 

Civil Aviation (TCCA), which is the 

airworthiness authority for Canada, has 

issued Airworthiness Directive CF– 

1992–26R2, dated September 1, 2010 

(referred to after this as ‘‘the MCAI’’), 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 [TCCA] 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 spar and rear spar, 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 

proposed AD. 

Relevant Service Information 

Bombardier Inc. has issued Alert 

Service Bulletin 215–A454, Revision 4, 

dated November 18, 2009. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 7 products of U.S. registry. 

The actions that are required by AD 

2005–18–05, Amendment 39–14245 (70 

FR 52009, September 1, 2005) and 

retained in this proposed AD take about 

17 work-hours per product, at an 

average labor rate of $85 per work hour. 

Based on these figures, the estimated 

cost of the currently required actions is 

$1,445 per product. 

We estimate that it would take about 

6 work-hour per product to comply with 

the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$3,570, or $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 480 work-hours for a cost of 

$40,800 per product. We have received 

no definitive data that would enable us 

to provide a parts cost estimate for the 

on-condition requirement specified in 

this proposed AD. We have no way of 

determining the number of products 

that may need these actions. 

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 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 

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6690 Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this 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); and 

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 proposed AD 

and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 Amendment 39–14245 (70 FR 

52009, September 1, 2005) and adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA–2012– 

0109; Directorate Identifier 2010–NM– 

244–AD. 

(a) Comments Due Date 

We must receive comments by March 26, 

2012. 

(b) Affected ADs 

This AD supersedes AD 2005–18–05, 

Amendment 39–14245 (70 FR 52009, 

September 1, 2005). 

(c) Applicability 

This AD applies to the Bombardier Inc. 

airplanes; certificated in any category; as 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model CL–215–1A10 (Water Bomber) 

airplanes, serial numbers 1001 through 1125 

inclusive. 

(2) Model CL–215–6B11 (CL215T Variant) 

airplanes, serial numbers 1056 through 1125 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking found outside the inspection area. 

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. 

(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. 

Restatement of Certain Requirements of AD 

98–04–08, Amendment 39–10321 (63 FR 

7640, February 17, 1998), With New Service 

Information 

(g) Initial Inspection of AD 98–04–08, 

Amendment 39–10321 (63 FR 7640, 

February 17, 1998), With New Threshold 

At the time specified in paragraph (h) of 

this AD: Perform an ultrasonic inspection to 

detect cracking of the lower cap of the wing 

front and rear spars at wing station 51, in 

accordance with the Accomplishment 

Instructions of Canadair Alert Service 

Bulletin 215–A463, Revision 1, dated May 

25, 1995, or Bombardier Alert Service 

Bulletin 215–A463, Revision 2, dated March 

13, 2001 (for the front spar); and Canadair 

Alert Service Bulletin 215–A454, Revision 1, 

dated May 25, 1995, Bombardier Alert 

Service Bulletin 215–A454, Revision 2, dated 

January 27, 1999, Bombardier Alert Service 

Bulletin 215–A454, Revision 3, dated March 

13, 2001, or Bombardier Alert Service 

Bulletin 215–A454, Revision 4, dated 

November 18, 2009 (for the rear spar). As of 

the effective date of this AD, the inspection 

must be done in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A463, Revision 2, 

dated March 13, 2001 (for the front spar); and 

Bombardier Alert Service Bulletin 215–A454, 

Revision 3, dated March 13, 2001, or 

Bombardier Alert Service Bulletin 215–A454, 

Revision 4, dated November 18, 2009 (for the 

rear spar). 

(h) Compliance Times 

Do the inspections required by paragraph 

(g) of this AD at the earlier of the times 

specified in paragraphs (h)(1) and (h)(2) of 

this AD. 

(1) Prior to the accumulation of 3,000 total 

flight hours, or within 25 flight hours after 

March 4, 1998 (the effective date of AD 98– 

04–08, Amendment 39–10321 (63 FR 7640, 

February 17, 1998)), whichever occurs later. 

(2) At the later of the times specified in 

paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. 

(i) Prior to the accumulation of 2,500 total 

flight hours, or 8,000 total water drops, 

whichever occurs first. 

(ii) Within 50 flight hours or 150 water 

drops after October 6, 2005 (the effective date 

of AD 2005–18–05, Amendment 39–14245 

(70 FR 52009, September 1, 2005), whichever 

occurs first. 

(i) Repetitive Inspections With New Intervals 

Repeat the ultrasonic inspection specified 

in paragraph (g) of this AD at the times 

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

AD, as applicable. 

(1) For airplanes on which any ultrasonic 

inspection required by paragraph (a) of AD 

98–04–08, Amendment 39–10321 (63 FR 

7640, February 17, 1998), has been done 

before October 6, 2005: Within 600 flight 

hours after the last ultrasonic inspection, do 

the ultrasonic inspection specified in 

paragraph (g) of this AD. Repeat the 

ultrasonic inspection specified in paragraph 

(g) of this AD thereafter at intervals not to 

exceed 600 flight hours or 2,000 water drops, 

whichever occurs first. 

(2) For airplanes on which the ultrasonic 

inspection required by paragraph (a) of AD 

98–04–08, Amendment 39–10321 (63 FR 

7640, February 17, 1998), has not been done 

before October 6, 2005: After accomplishing 

the initial ultrasonic inspection specified in 

paragraph (g) of this AD, repeat the ultrasonic 

inspection specified in paragraph (g) of this 

AD thereafter at intervals not to exceed 600 

flight hours or 2,000 water drops, whichever 

occurs first. 

Restatement of Requirements of AD 2005– 

18–05, Amendment 39–14245 (70 FR 52009, 

September 1, 2005), With New Service 

Information 

(j) Ultrasonic Inspection 

At the later of the times specified in 

paragraphs (j)(1) and (j)(2) of this AD, do an 

ultrasonic inspection for cracks of the wing 

lower skin, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A454, Revision 3, 

dated March 13, 2001; or Bombardier Alert 

Service Bulletin 215–A454, Revision 4, dated 

November 18, 2009. Thereafter, do the 

ultrasonic inspection for cracks of the wing 

lower skin at the times specified for the 

ultrasonic inspection in paragraph (i) of this 

AD. 

(1) Within 50 flight hours or 150 water 

drops after October 6, 2005, whichever 

occurs first. 

(2) Before further flight after accomplishing 

the first ultrasonic inspection required by 

paragraph (g) or (i) of this AD after October 

6, 2005. 

(k) Cracking Detected 

If any cracking is detected during any 

inspection required by paragraph (g), (i), or 

(j) of this AD, before further flight, 

accomplish paragraphs (k)(1) and (k)(2) of 

this AD. 

(1) Rework the lower cap of the front or 

rear spar, as applicable, in accordance with 

the Accomplishment Instructions of 

Bombardier Alert Service Bulletin 215–A463, 

Revision 2, dated March 13, 2001 (for the 

front spar); and Bombardier Alert Service 

Bulletin 215–A454, Revision 3, dated March 

13, 2001; or Bombardier Alert Service 

Bulletin 215–A454, Revision 4, dated 

November 18, 2009 (for the rear spar). 

(2) After doing the rework specified in 

paragraph (k)(1) of this AD, do a general 

visual inspection, from inside the wing box, 

to detect cracks of the front spar web or rear 

spar web, as applicable, and the lower skin 

area, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A463, Revision 2, 

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dated March 13, 2001 (for the front spar); and 

Bombardier Alert Service Bulletin 215–A454, 

Revision 3, dated March 13, 2001 (for the rear 

spar); or Bombardier Alert Service Bulletin 

215–A454, Revision 4, dated November 18, 

2009 (for the rear spar). If any cracking is 

detected: Before further flight, repair in 

accordance with a method approved by the 

Manager, New York Aircraft Certification 

Office (ACO), FAA; or Transport Canada 

Civil Aviation (TCCA) (or its delegated 

agent). 

(l) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(l) Actions accomplished before October 6, 

2005, in accordance with Canadair Alert 

Service Bulletin 215–A463, dated April 8, 

1993; Canadair Alert Service Bulletin 215– 

A463, Revision 1, dated May 25, 1995; 

Canadair Alert Service Bulletin 215–A454, 

dated October 13, 1993; Canadair Alert 

Service Bulletin 215–A454, Revision 1, dated 

May 25, 1995; Bombardier Alert Service 

Bulletin 215–A454, Revision 2, dated January 

27, 1999; are considered acceptable for 

compliance with the corresponding actions 

specified in this AD. 

(2) Actions accomplished before October 6, 

2005, in accordance with Bombardier Alert 

Wire 215–A454, dated December 23, 1992; 

and Bombardier Alert Wire 215–A463, dated 

March 26, 1993; are considered acceptable 

for compliance with the corresponding 

actions specified in this AD. 

(m) Reporting Requirement 

For any inspection required by AD 2005– 

18–05, Amendment 39–14245 (70 FR 52009, 

September 1, 2005), that is accomplished 

after October 6, 2005, within 30 days after 

accomplishing the inspection, submit a 

report of any inspection results (both positive 

and negative findings) to Bombardier, Inc., 

Canadair, Aerospace Group, P.O. Box 6087, 

Station Centre-ville, Montreal, Quebec H3C 

3G9, Canada; or to Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec H4S 

1Y9, Canada; telephone 514–855–5000; fax 

514–855–7401; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. As of the effective 

date of this AD, submit reports to 

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

Dorval, Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

New Requirements of This AD 

(n) Ultrasonic Inspection of the Rear Spar 

Lower Cap 

Within the compliance time specified in 

paragraph (p) of this AD: Perform an 

ultrasonic inspection to detect cracking of the 

right and left wing rear spar lower cap 

between wing station (WS) 51.00 and WS 

49.50, in accordance with paragraph 2.C., 

‘‘Part A,’’ of the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A454, Revision 4, dated 

November 18, 2009. Repeat the ultrasonic 

inspection thereafter at intervals not to 

exceed 600 flight hours or 2,000 water drops, 

whichever comes first. Accomplishment of 

the actions in this paragraph terminates the 

inspection requirements of the lower cap of 

the wing rear spars at wing station 51.00 of 

paragraph (g) of this AD. Accomplishment of 

the actions in this paragraph does not 

terminate the inspection requirements of the 

lower cap of the front wing spars at wing 

station 51.00 required by paragraph (g) of this 

AD. 

(1) If any crack is found in the rear spar 

lower cap, before further flight, do a general 

visual inspection for cracks from inside the 

wing box, of the areas of the rear spar web 

and the wing lower skin adjacent to the crack 

in the rear spar lower cap, in accordance 

with paragraph 2.C., ‘‘Part A,’’ of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A454, Revision 4, 

dated November 18, 2009. 

(2) If any cracking is detected during any 

ultrasonic or general visual inspection 

required by paragraph (n) of this AD, before 

further flight, repair in accordance with a 

method approved by the Manager, New York 

ACO, FAA; or TCCA (or its delegated agent). 

(o) Ultrasonic Inspection of the Lower Wing 

Skin 

Within the compliance time specified in 

paragraph (p) of this AD: Perform an 

ultrasonic inspection to detect cracking of the 

wing lower skin underneath the drag angle 

between the front spar and the rear spar at 

the left and right WS 51.00, in accordance 

with paragraph 2.D., ‘‘Part B,’’ of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A454, Revision 4, 

dated November 18, 2009. Do the ultrasonic 

inspection thereafter at intervals not to 

exceed 600 flight hours or 2,000 water drops, 

whichever comes first. Accomplishment of 

the actions in this paragraph terminates the 

requirements of paragraph (j) of this AD. 

(1) If any crack is found in the wing lower 

skin, before further flight, do a general visual 

inspection for cracks from inside the wing 

box, i.e., the stringers adjacent to the skin 

crack in accordance with paragraph 2.D., 

‘‘Part B,’’ of the Accomplishment Instructions 

of Bombardier Alert Service Bulletin 215– 

A454, Revision 4, dated November 18, 2009. 

. 

(2) If any cracking is detected during any 

ultrasonic or general visual inspection 

required by paragraph (o) of this AD, before 

further flight, repair in accordance with a 

method approved by the Manager, New York 

ACO, FAA; or TCCA (or its delegated agent). 

(p) Compliance Times for Paragraphs (n) 

and (o) of This AD 

At the later of the times specified in 

paragraphs (p)(1) and (p)(2) of this AD. 

(1) Prior to the accumulation of 2,500 total 

flight hours, or 8,000 total water drops, 

whichever occurs first. 

(2) Within 50 flight hours or 150 water 

drops after the effective date of this AD, 

whichever occurs first. 

(q) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Inspections accomplished at WS 51.00 

before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A454, Revision 3, dated March 

13, 2001, within the last 550 flight hours or 

1,850 water drops, are considered acceptable 

for compliance with the corresponding action 

specified in paragraph (o) of this AD. 

(r) Reporting Requirements With New 

Address 

At the applicable time specified in 

paragraph (r)(1) or (r)(2) of this AD, submit 

a report of the findings (both positive and 

negative) of the inspection required by 

paragraphs (n) and (o) of this AD to 

Bombardier, Inc., in accordance with 

Bombardier Alert Service Bulletin 215–A454, 

Revision 4, dated November 18, 2009. 

(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. 

(s) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; phone: 516–228–7300; fax: 516–794– 

5531. 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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

6692 Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Proposed Rules 

be directed to the FAA at: 800 Independence 

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

Information Collection Clearance Officer, 

AES–200. 

(t) Related Information 

Refer to MCAI Airworthiness Directive CF– 

1992–26R2, dated September 1, 2010, and the 

following service information for related 

information. 

(1) Bombardier Alert Service Bulletin 215– 

A463, Revision 2, dated March 13, 2001. 

(2) Bombardier Alert Service Bulletin 215– 

A454, Revision 3, dated March 13, 2001. 

(3) Bombardier Alert Service Bulletin 215– 

A454, Revision 4, dated November 18, 2009. 

Issued in Renton, Washington, on January 

26, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–3031 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–2012–0110; Directorate 

Identifier 2011–NM–148–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 adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes equipped with analog 

transient suppression devices (ATSDs) 

installed in accordance with 

Supplemental Type Certificate number 

ST00146BO. This proposed AD was 

prompted by multiple reports of 

corrosion on ATSDs. This proposed AD 

would require revising the maintenance 

program to incorporate certain 

limitations. We are proposing this AD to 

detect and correct corrosion on ATSDs, 

which could result in the loss of high 

voltage transient protection (e.g., 

lightning protection) in the fuel tanks 

and consequent fuel tank explosion and 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 26, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 proposed AD, contact Goodrich 

Corporation, Sensors and Integrated 

Systems, 100 Panton Road, Vergennes, 

Vermont 05491; phone: 802–877–4580; 

fax: 802–877–4444; email: 

les.blades@goodrich.com; Internet: 

http://www.goodrich.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: 

Marc Ronell, Aerospace Engineer, 

Engine and Propeller Directorate, ANE– 

150, FAA, New England Aircraft 

Certification Office (ACO), 12 New 

England Executive Park, Burlington, 

Massachusetts 01803; phone: 781–238– 

7776; fax: 781–238–7170; email: 

marc.ronell@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0110; Directorate Identifier 2011– 

NM–148–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 

We have received at least six reports 

of corrosion on the housings of ATSDs. 

This condition, if not corrected, could 

result in the loss of high voltage 

transient protection (e.g., lightning 

protection) in the fuel tanks and 

consequent fuel tank explosion and loss 

of the airplane. 

Relevant Service Information 

We have reviewed Goodrich Principal 

Instructions for Continued 

Airworthiness Manual for the Analog 

Transient Suppression Device 

Installation Applicable to Boeing 737– 

100 through -500 Airplanes 

Supplemental Type Certificate— 

ST00146BO, Document T3044–0010– 

0101, Revision D, dated September 26, 

2011, which describes various 

limitations, including Critical Design 

Control Limitations (CDCCL), 

inspections, and checks of the ATSD, 

ground straps, and safe-side harness. 

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 require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 384 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

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