20520 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 

(e) Required Actions 

Before further flight, replace any affected 

blade with an airworthy blade, defined as 

one that has a part number and a serial 

number not listed in the Applicability 

section of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

(2) For operations conducted under a Part 

119 operating certificate or under Part 91, 

Subpart K, we suggest that you notify your 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate holding 

district office, before operating any aircraft 

complying with this AD through an AMOC. 

(g) Additional Information 

(1) Agusta Bollettino Tecnico 412–130, 

dated December 20, 2010, which is not 

incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Agusta Westland, Customer 

Support & Services, Via Per Tornavento 15, 

21019 Somma Lombardo (VA) Italy, ATTN: 

Giovanni Cecchelli; telephone 39–0331– 

711133; fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. You may review a copy of the 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(2) The subject of this AD is addressed in 

the European Aviation Safety Agency 

Emergency AD No.: 2010–0272–E, dated 

December 22, 2010. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, tail rotor blades. 

Issued in Fort Worth, Texas, on March 26, 

2012. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–8058 Filed 4–4–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1064; Directorate 

Identifier 2011–NM–075–AD; Amendment 

39–16984; AD 2012–06–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model BD–100–1A10 (Challenger 

300) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Bombardier, Inc. Model BD–100–1A10 

(Challenger 300) airplanes. This AD was 

prompted by reports that the horizontal 

stabilizer trim actuator (HSTA) no-back 

and the number 1 motor brake assembly 

(MBA) can both fail dormant. This AD 

requires revising the airplane 

maintenance schedule to include new 

functional tests of the HSTA no-back 

and HSTA brake system. We are issuing 

this AD to prevent dormant failure of 

the HSTA no-back and the number 1 

MBA, which along with additional 

component failure could result in an 

uncontrollable horizontal stabilizer 

surface runaway without the ability to 

retrim, and consequent loss of the 

airplane. 

DATES: This AD becomes effective May 

10, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 10, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov or in person at the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; 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 October 11, 2011 (76 FR 

62669), and proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

It was discovered that the Horizontal 

Stabilizer Trim Actuator (HSTA) No Back 

and the Number 1 Motor Brake Assembly 

(MBA) can both fail dormant. A failure of the 

HSTA No Back and the Brake System along 

with additional component failure could 

result in an uncontrollable horizontal 

stabilizer surface runaway without the ability 

to retrim. This condition, if not corrected, 

could lead to the loss of the aeroplane. 

As a result, new Airworthiness Limitation 

Tasks, consisting of a functional test of the 

HSTA No Back and a functional test of the 

HSTA Brake System, have been introduced to 

ensure that a dormant failure of either 

component is detected and corrected. 

This [TCCA] directive mandates the 

revision of the approved maintenance 

schedule to include these new tasks, 

including phase-in schedules. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the single comment 

received. 

Request To Revise Number of U.S.- 

Registered Airplanes 

The commenter, Matthew B. Mitchell, 

stated that the number of U.S.-registered 

Model BD–100–1A10 airplanes exceeds 

the 76 airplanes shown in the Costs of 

Compliance section of this AD, and 

should be 238 airplanes, to agree with 

Aircraft Geometric Height Measurement 

Element (AGHME) figures. 

We agree to revise the number of U.S.- 

registered airplanes used to determine 

the cost estimate in this AD. We have 

confirmed with Bombardier, Inc., that 

217 Model BD–100–1A10 airplanes are 

registered in the U.S. We have changed 

the figures in the ‘‘Costs of Compliance’’ 

section of this AD accordingly. 

Additional Changes Made to This AD 

We have redesignated Note 1 of the 

NPRM (76 FR 62669, October 11, 2011) 

as paragraph (c)(2) of this AD, paragraph 

(c) of the NPRM as paragraph (c)(1) of 

this AD, and Note 2 of the NPRM as 

Note 1 to paragraphs (g) and (h) of this 

AD. We have also relocated Note 1 of 

this AD to follow paragraph (g) of this 

AD. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 


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Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 20521 

with the changes described previously. 

We 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 will affect 

217 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

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

be $18,445, or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov; or in person at the Docket 

Operations office between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains the NPRM (76 FR 62669, 

October 11, 2011), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2012–06–03 Bombardier, Inc.: Amendment 

39–16984. Docket No. FAA–2011–1064; 

Directorate Identifier 2011–NM–075–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 10, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all Bombardier, Inc. 

Model BD–100–1A10 (Challenger 300) 

airplanes, certificated in any category. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new inspections. Compliance with these 

tasks is required by 14 CFR 91.403(c). For 

airplanes that have been previously 

modified, altered, or repaired in the areas 

addressed by these inspections, the operator 

may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (j) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

(e) Reason 

This AD was prompted by reports that the 

horizontal stabilizer trim actuator (HSTA) noback and the number 1 motor brake assembly 

(MBA) can both fail dormant. We are issuing 

this AD to prevent dormant failure of the 

HSTA no-back and the number 1 MBA, 

which along with additional component 

failure could result in an uncontrollable 

horizontal stabilizer surface runaway without 

the ability to retrim, and consequent loss 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. 

(g) Add Task 27–40–00–107 to the 

Maintenance Program 

Within 30 days after the effective date of 

this AD: Revise the maintenance program by 

incorporating Task 27–40–00–107, 

‘‘Functional Test of the Horizontal Stabilizer 

Trim Actuator (HSTA) No Back,’’ in 

accordance with Bombardier Temporary 

Revision 5–2–59, dated November 25, 2010, 

to Section 5–10–40, of Part 2, of the 

Bombardier Challenger 300 BD–100 Time 

Limits/Maintenance Checks Manual. For this 

task, the initial compliance time starts at the 

applicable time specified in paragraph (g)(1) 

or (g)(2) of this AD. 

Note 1 to paragraphs (g) and (h) of this 

AD: The maintenance program revision 

required by paragraphs (g) and (h) of this AD 

may be done by inserting a copy of 

Bombardier Temporary Revision 5–2–59, 

dated November 25, 2010, into Section 5–10– 

40, of Part 2, of the Bombardier Challenger 

300 BD–100 Time Limits/Maintenance 

Checks Manual. When this Temporary 

Revision has been included in the general 

revisions of Section 5–10–40, of Part 2, of the 

Bombardier Challenger 300 BD–100 Time 

Limits/Maintenance Checks Manual, the 

general revisions may be inserted in Section 

5–10–40, of Part 2, of the Bombardier 

Challenger 300 BD–100 Time Limits/ 

Maintenance Checks Manual, provided that 

the relevant information in the general 

revision is identical to that in Bombardier 

Temporary Revision 5–2–59, dated 

November 25, 2010, to Section 5–10–40, of 

Part 2, of the Bombardier Challenger 300 BD– 

100 Time Limits/Maintenance Checks 

Manual. 

(1) For HSTAs with 2,600 or fewer total 

flight hours on the HSTA as of the effective 

date of this AD: Prior to the accumulation of 

3,000 total flight hours on the HSTA. 

(2) For HSTAs with more than 2,600 total 

flight hours on the HSTA as of the effective 

date of this AD: Within 400 flight hours or 

6 months after the effective date of this AD, 

whichever occurs first. 

(h) Add Task 27–41–05–105 to the 

Maintenance Program 

Within 30 days after the effective date of 

this AD, whichever occurs later: Revise the 

maintenance program by incorporating Task 

27–41–05–105, ‘‘Functional Test of the 

Horizontal Stabilizer Trim Actuator (HSTA) 

Brake System,’’ in accordance with 


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20522 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 

Bombardier Temporary Revision 5–2–59, 

dated November 25, 2010, to Section 5–10– 

40, of Part 2, of the Bombardier Challenger 

300 BD–100 Time Limits/Maintenance 

Checks Manual. For this task, the initial 

compliance time starts at the applicable time 

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

AD. 

(1) For airplanes with 400 or fewer total 

flight hours as of the effective date of this 

AD: Prior to the accumulation of 800 total 

flight hours. 

(2) For airplanes with more than 400 total 

flight hours as of the effective date of this 

AD: Within 400 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first. 

(i) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraphs (g) and (h) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j)(1) of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 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. 

(k) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2011–05, dated March 24, 2011; 

and Bombardier Temporary Revision 5–2–59, 

dated November 25, 2010, to Section 5–10– 

40, of Part 2, of the Bombardier Challenger 

300 BD–100 Time Limits/Maintenance 

Checks Manual; for related information. 

(l) 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) Bombardier Temporary Revision 5–2– 

59, dated November 25, 2010, to Section 5– 

10–40, of Part 2, of the Bombardier 

Challenger 300 BD–100 Time Limits/ 

Maintenance Checks Manual. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu 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. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(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 Renton, Washington, on March 9, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–8041 Filed 4–4–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0723; Directorate 

Identifier 2010–NM–080–AD; Amendment 

39–16978; AD 2012–05–06] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company 

Model L–1011–385–1, L–1011–385–1– 

14, and L–1011–385–1–15 airplanes. 

That AD currently requires 

implementation of a Supplemental 

Inspection Document (SID) program of 

structural inspections to detect fatigue 

cracking, and repair if necessary, to 

ensure continued airworthiness of these 

airplanes as they approach the 

manufacturer’s original fatigue design 

life goal. This new AD adds Model L– 

1011–385–3 airplanes to the 

applicability, changes certain inspection 

thresholds, adds three new structurally 

significant details (SSDs), and removes 

an SSD that has been addressed by a 

different AD. This AD was prompted by 

an evaluation by the manufacturer of 

usage and flight data that provided 

additional information about certain 

SSDs where fatigue damage is likely to 

occur. We are issuing this AD to prevent 

fatigue cracking that could compromise 

the structural integrity of these 

airplanes. 

DATES: This AD is effective May 10, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 10, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 2, 1995 (60 FR 

51713, October 3, 1995). 

ADDRESSES: For service information 

identified in this AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, 

Georgia 30063; phone: 770–494–5444; 

fax 770–494–5445; email 

ams.portal@lmco.com; Internet http:// 

www.lockheedmartin.com/ams/tools/ 

TechPubs.html. 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 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: Carl 

Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: 404–474–5554; fax 404– 

474–5606; email: Carl.W.Gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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