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01, dated June 19, 2012 (for Model ERJ 190– 

100 STD, –100 LR, –100 ECJ, and –100 IGW 

airplanes; and Model ERJ 190–200 STD, –200 

LR, and –200 IGW airplanes). 

(1) Do a general visual inspection of the 

HRD bottle to determine if it is correctly 

installed and if the pressure switch is in the 

correct position. If the bottle is not correctly 

installed or the pressure switch is in the 

incorrect position, before further flight, 

remove and re–install the HRD bottle. 

(2) Inspect the HRD and LRD bottle 

discharge heads to determine the part 

number. If the part number of the discharge 

heads is not the part number specified in 

Figure 3 of EMBRAER Service Bulletin 170– 

26–0011, Revision 01, dated June 19, 2012 

(for Model ERJ 170–100 LR, –100 STD, –100 

SE, and –100 SU airplanes; and Model ERJ 

170–200 LR, –200 SU, and –200 STD 

airplanes); EMBRAER Service Bulletin 190– 

26–0011, Revision 01, dated June 19, 2012 

(for Model ERJ 190–100 STD, –100 LR, –100 

ECJ, and –100 IGW airplanes; and Model ERJ 

190–200 STD, –200 LR, and –200 IGW 

airplanes); or EMBRAER Service Bulletin 

190LIN–26–0006, Revision 01, dated June 19, 

2012 (for Model ERJ 190–100 STD, –100 LR, 

–100 ECJ, and –100 IGW airplanes; and 

Model ERJ 190–200 STD, –200 LR, and –200 

IGW airplanes), before further flight, replace 

the discharge bottle with a discharge bottle 

having the same part number. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2768; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA–approved. Corrective 

actions are considered FAA–approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

(1) Refer to MCAI Brazilian Airworthiness 

Directives 2012–07–01 and 2012–07–02, both 

effective July 30, 2012, and the service 

bulletins identified in paragraphs (j)(1)(i), 

(j)(1)(ii), and (j)(1)(iii) of this AD, for related 

information. 

(i) EMBRAER Service Bulletin 170–26– 

0011, Revision 01, dated June 19, 2012. 

(ii) EMBRAER Service Bulletin 190–26– 

0011, Revision 01, dated June 19, 2012. 

(iii) EMBRAER Service Bulletin 190LIN– 

26–0006, Revision 01, dated June 19, 2012. 

(2) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170–Putim–12227–901 Sa ̃o Jose 

dos Campos–SP–BRASIL; telephone +55 12 

3927–5852 or +55 12 3309–0732; fax +55 12 

3927–7546; email distrib@embraer.com.br; 

Internet http://www.flyembraer.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

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

Issued in Renton, Washington, on October 

5, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25459 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1078; Directorate 

Identifier 2011–NM–012–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics 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 all Lockheed Martin 

Corporation/Lockheed Martin 

Aeronautics Company Model L–1011 

series airplanes. The existing AD 

currently requires repetitive inspections 

to detect corrosion or fatigue cracking of 

certain structural elements of the 

airplane; corrective actions if necessary; 

and incorporation of certain structural 

modifications. Since we issued that AD, 

we have received reports of small cracks 

in additional areas outside those 

addressed in the existing AD, prior to 

the inspection threshold required by the 

existing AD. This proposed AD would 

reduce certain compliance times for the 

initial inspection, and the repetitive 

inspection interval for certain airplanes. 

We are proposing this AD to prevent 

corrosion or fatigue cracking of certain 

structural elements, which could result 

in reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 30, 

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 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; telephone 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 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: 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– 

474–5605; email: carl.w.gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


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this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–1078; Directorate Identifier 

2011–NM–012–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 July 8, 2005, we issued AD 2005– 

15–01, Amendment 39–14191 (70 FR 

42262, July 22, 2005), for all Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Model L–1011 

series airplanes. That AD requires 

repetitive inspections to detect 

corrosion or fatigue cracking of certain 

structural elements of the airplane; 

corrective actions if necessary; and 

incorporation of certain structural 

modifications. That AD resulted from 

new recommendations related to 

incidents of fatigue cracking and 

corrosion in transport category airplanes 

that are approaching or have exceeded 

their economic design goal. We issued 

that AD to prevent corrosion or fatigue 

cracking of certain structural elements, 

which could result in reduced structural 

integrity of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2005–15–01, 

Amendment 39–14191 (70 FR 42262, 

July 22, 2005), we have received reports 

of small cracks found outside the areas 

addressed by the existing AD. 

Specifically, these cracks were found 

from inner wing station (IWS) 477.70 to 

IWS 372.64 (inboard) and from outer 

wing station (OWS) 52.2 to OWS 296.5 

(outboard). 

Relevant Service Information 

AD 2005–15–01, Amendment 39– 

14191 (70 FR 42262, July 22, 2005), 

refers to Lockheed Tristar L–1011 

Service Bulletin 093–51–041, Revision 

1, dated March 3, 2000 (a ‘‘collector 

service bulletin’’), as the appropriate 

source of service information for the 

required actions. This service bulletin 

has since been revised. We have 

reviewed Lockheed Service Bulletin 

093–51–041, Revision 2, dated March 

30, 2010, which, in turn, refers to 

Lockheed Service Bulletin 093–57–195, 

now at Revision 4, dated March 17, 

2010. 

Lockheed Service Bulletin 093–57– 

195, Revision 4, dated March 17, 2010, 

includes the following changes: 

• Supersedes Lockheed Service 

Bulletin 093–57–069, Revision 4, dated 

October 5, 1998. 

• Reduces the initial inspection 

threshold to 15,000 flight cycles; or 

15,000 flight cycles after incorporation 

of Lockheed Service Bulletin 093–57– 

069, Revision 4, dated October 5, 1998. 

• Reduces the repetitive inspection 

interval to 1,750 flight cycles for Model 

L–1011–385–3 airplanes. 

• Changes the fastener hole cold 

working procedure from ‘‘FTI–LCC– 

8701’’ to ‘‘FTI–LASC–51–20–01.’’ 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2005–15–01, 

Amendment 39–14190 (70 FR 42262, 

July 22, 2005). This proposed AD would 

reduce the initial inspection threshold 

for certain airplanes for accomplishment 

of the actions specified in Lockheed 

Service Bulletin 093–57–195, Revision 

4, dated March 17, 2010, and would 

reduce the repetitive inspection interval 

for Model L–1011–385–3 airplanes. This 

proposed AD would also require 

accomplishing the actions specified in 

the service information described 

previously. 

Changes to Existing AD 

This proposed AD would retain all 

requirements of AD 2005–15–01, 

Amendment 39–14191 (70 FR 42262, 

July 22, 2005). Since AD 2005–15–01 

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 2005–15–01, 

Amendment 

39-14190 (70 FR 

42262, 

July 22, 2005) 

Corresponding 

requirement in this 

proposed AD 

paragraph (a) paragraph (g). 

paragraph (b) paragraph (h). 

paragraph (c) paragraph (i). 

In addition, we have removed 

paragraph (b)(2) from AD 2005–15–01, 

Amendment 39–14190 (70 FR 42262, 

July 22, 2005), and added a new 

sentence to paragraph (h)(3) of this 

proposed AD to specify that information 

on additional methods of compliance 

can be obtained from the Manager, 

Atlanta Aircraft Certification Office 

(ACO). We might decide to approve 

certain sections of the Lockheed L–1011 

structural repair manual as an 

alternative method of compliance with 

this proposed AD, as provided by 

paragraph (l) of this proposed AD. 

We have also revised the applicability 

of the existing AD 2005–15–01, 

Amendment 39–14190 (70 FR 42262, 

July 22, 2005), to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Costs of Compliance 

We estimate that this proposed AD 

affects 26 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 

Inspections [retained actions from existing AD 

2005–15–01, Amendment 39–14191 (70 FR 

42262, July 22, 2005)].

129 work-hours × $85 

per hour = $10,965 

per inspection cycle.

$0 $10,965 per inspection 

cycle.

$285,090 per inspection 

cycle. 

Modification [retained action from existing AD 

2005–15–01, Amendment 39–14191 (70 FR 

42262, July 22, 2005)].

614 work-hours × $85 

per hour = $52,190.

$142,275 $194,465 ...................... $5,056,194. 


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We have received no definitive data 

that would enable us to provide cost 

estimates for the retained on-condition 

actions specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We 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. 

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) 

2005–15–01, Amendment 39–14190 (70 

FR 42262, July 22, 2005), and adding the 

following new AD: 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company: Docket 

No. FAA–2012–1078; Directorate 

Identifier 2011–NM–012–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by November 30, 2012. 

(b) Affected ADs 

This AD supersedes AD 2005–15–01, 

Amendment 39–14190 (70 FR 42262, July 22, 

2005). 

(c) Applicability 

This AD applies to all Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company Model L–1011–385–1, L–1011– 

385–1–14, L–1011–385–1–15, and L–1011– 

385–3 airplanes; certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 51, Standard practices/structures; 52, 

Doors; 53, Fuselage; 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of small 

cracks in additional areas outside those 

addressed in the existing AD (AD 2005–15– 

01, Amendment 39–14190 (70 FR 42262, July 

22, 2005)), prior to the inspection threshold 

required by the existing AD. We are issuing 

this AD to prevent corrosion or fatigue 

cracking of certain structural elements, 

which could result in reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections With Revised 

Service Information and Reduced 

Compliance Times 

This paragraph restates the inspection 

required by paragraph (a) of AD 2005–15–01, 

Amendment 39–14190 (70 FR 42262, July 22, 

2005), with revised service information and 

reduced compliance times for paragraph 

(g)(16) of this AD. At the time specified in 

the ‘‘Initial Compliance Time’’ column of 

table 1 to paragraph (g) of this AD, perform 

structural inspections to detect corrosion or 

fatigue cracking of certain structural elements 

of the airplane, in accordance with the 

applicable service bulletins listed under 

‘‘Service Bulletin Number, Revision, and 

Date’’ in tables I and II of Lockheed Tristar 

L–1011 Service Bulletin 093–51–041, 

Revision 1, dated March 3, 2000, or Revision 

2, dated March 30, 2010. As of the effective 

date of this AD, only Lockheed Tristar L– 

1011 Service Bulletin 093–51–041, Revision 

2, dated March 30, 2010, may be used for the 

actions required by this paragraph. 

Thereafter, repeat the inspections at intervals 

specified in the ‘‘Repetitive Intervals’’ 

column of table 1 to paragraph (g) of this AD. 

TABLE 1 TO PARAGRAPH (g) OF THIS AD 

Lockheed TriStar L–1011 

Service Bulletin 

Initial compliance time 

(whichever occurs later between the times in ‘‘Inspection 

Threshold’’ and ‘‘Grace Period’’) Repetitive intervals Terminating action 

Inspection threshold Grace period 

(1) 093–53–269, Revision 

1, dated October 28, 

1997; or.

Before the accumulation of 

8,000 total flight cycles 

or 15,000 total flight 

hours, whichever occurs 

first.

Within 6,450 flight cycles 

or 5 years after August 

26, 2005 (the effective 

date of AD 2005–15–01, 

Amendment 39–14190 

(70 FR 42262, July 22, 

2005)), whichever occurs first.

At intervals not to exceed 

6,450 flight cycles or 5 

years, whichever occurs 

first.

(None). 


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TABLE 1 TO PARAGRAPH (g) OF THIS AD—Continued 

Lockheed TriStar L–1011 

Service Bulletin 

Initial compliance time 

(whichever occurs later between the times in ‘‘Inspection 

Threshold’’ and ‘‘Grace Period’’) Repetitive intervals Terminating action 

Inspection threshold Grace period 

(2) 093–53–274, dated 

May 28, 1997.

Within 14 months after August 26, 2005 (the effective date of AD 2005– 

15–01, Amendment 39– 

14190 (70 FR 42262, 

July 22, 2005)).

(None) ............................... At intervals not to exceed 

14 months.

(None). 

(3) 093–53–275, dated December 10, 1996.Within 6,450 flight cycles 

or 5 years after August 

26, 2005 (the effective 

date of AD 2005–15–01, 

Amendment 39–14190 

(70 FR 42262, July 22, 

2005)), whichever occurs first.

(None) ............................... (None) ............................... (None). 

(4) 093–53–276, dated 

June 17, 1996.

At the next Corrosion Prevention and Control Program (CPCP) inspection 

after August 26, 2005 

(the effective date of AD 

2005–15–01, Amendment 39–14190 (70 FR 

42262, July 22, 2005)).

(None) ............................... At intervals not to exceed 

the next CPCP inspection.

(None). 

(5) 093–57–085, Revision 

1, dated December 1, 

1997.

Before the accumulation of 

26,000 total flight cycles 

or 48,000 total flight 

hours, whichever occurs 

first.

Within 1,800 flight cycles 

or 3,300 flight hours 

after August 26, 2005 

(the effective date of AD 

2005–15–01, Amendment 39–14190 (70 FR 

42262, July 22, 2005)), 

whichever occurs first.

At intervals not to exceed 

1,800 flight cycles or 

3,300 flight hours, 

whichever occurs first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–57–085, Basic 

Issue, dated May 7, 

1993; or Revision 1, 

dated December 1, 

1997. 

(6) 093–57–208, Revision 

1, dated October 28, 

1997.

Before the accumulation of 

18,000 total flight cycles.

Within 6,450 flight cycles 

or 5 years after August 

26, 2005 (the effective 

date of AD 2005–15–01, 

Amendment 39–14190 

(70 FR 42262, July 22, 

2005)), whichever occurs first.

At intervals not to exceed 

6,450 flight cycles or 5 

years, whichever occurs 

first.

(None). 

(7) 093–52–210, dated 

July 19, 1991.

Within 5,000 flight hours or 

18 months after August 

26, 2005 (the effective 

date of AD 2005–15–01, 

Amendment 39–14190 

(70 FR 42262, July 22, 

2005)), whichever occurs first.

(None) ............................... (None) ............................... (None). 

(8) 093–53–054, Revision 

1, dated August 12, 

1975.

Within 6,450 flight cycles 

or 5 years after August 

26, 2005 (the effective 

date of AD 2005–15–01, 

Amendment 39–14190 

(70 FR 42262, July 22, 

2005)), whichever occurs first.

(None) ............................... (None) ............................... (None). 

(9) 093–53–070, Revision 

3, dated September 19, 

1989.

Before the accumulation of 

6,000 total flight hours.

Within 1,500 flight hours 

after August 26, 2005 

(the effective date of AD 

2005–15–01, Amendment 39–14190 (70 FR 

42262, July 22, 2005)).

At intervals not to exceed 

3,000 flight hours.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–070, Basic 

Issue, dated September 

26, 1974; Revision 1, 

dated January 23, 1975; 

Revision 2, dated July 7, 

1975; or Revision 3, 

dated September 19, 

1989. 


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TABLE 1 TO PARAGRAPH (g) OF THIS AD—Continued 

Lockheed TriStar L–1011 

Service Bulletin 

Initial compliance time 

(whichever occurs later between the times in ‘‘Inspection 

Threshold’’ and ‘‘Grace Period’’) Repetitive intervals Terminating action 

Inspection threshold Grace period 

(10) 093–53–085, Revision 

3, dated December 15, 

1989.

Part I: Before the accumulation of 20,000 flight cycles or 37,000 total flight 

hours, whichever occurs 

first.

Part I: Within 1,600 flight 

cycles or 3,000 flight 

hours after August 26, 

2005 (the effective date 

of AD 2005–15–01, 

Amendment 39–14190 

(70 FR 42262, July 22, 

2005)), whichever occurs first.

Part I: At intervals not to 

exceed 1,600 flight cycles or 3,000 flight 

hours, whichever occurs 

first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–085, Basic 

Issue, dated September 

29, 1975; Revision 1, 

dated September 3, 

1976; or Revision 2, 

dated February 8, 1988. 

Part II: Before the accumulation of 30,000 flight cycles or 55,000 total flight 

hours, whichever occurs 

first.

Part II: Within 5,000 flight 

cycles or 9,200 flight 

hours after August 26, 

2005 (the effective date 

of AD 2005–15–01, 

Amendment 39–14190 

(70 FR 42262, July 22, 

2005)), whichever occurs first.

Part II: At intervals not to 

exceed 5,000 flight cycles or 9,200 flight 

hours, whichever occurs 

first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–085, Basic 

Issue, dated September 

29, 1975; Revision 1, 

dated September 3, 

1976; or Revision 2, 

dated February 8, 1988. 

(11) 093–53–086, Revision 

5, dated April 12, 1990.

Before the accumulation of 

9,000 flight cycles or 

10,000 flight hours, 

whichever occurs first.

Within 1,600 flight cycles 

or 3,000 flight hours 

after August 26, 2005 

(the effective date of AD 

2005–15–01, Amendment 39–14190 (70 FR 

42262, July 22, 2005)), 

whichever occurs first.

At intervals not to exceed 

1,600 flight cycles or 

3,000 flight hours, 

whichever occurs first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–086, Basic 

Issue, dated September 

26, 1975; Revision 1, 

dated November 12, 

1975; Revision 2, dated 

December 12, 1976; Revision 3, dated July 19, 

1977; Revision 4, dated 

July 8, 1985; or Revision 

5, dated April 12, 1990. 

(12) 093–53–110, Revision 

1, dated May 7, 1993.

Before the accumulation of 

22,000 total flight cycles 

or 40,000 total flight 

hours, whichever occurs 

first.

Within 2,200 flight cycles 

or 4,000 flight hours 

after August 26, 2005 

(the effective date of AD 

2005–15–01, Amendment 39–14190 (70 FR 

42262, July 22, 2005)), 

whichever occurs first.

At intervals not to exceed 

2,200 flight cycles or 

4,000 flight hours, 

whichever occurs first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–110, Basic 

Issue, dated August 19, 

1991; or Revision 1, 

dated May 7, 1993. 

(13) Change Notification 

093–53–260, CN4, dated 

May 8, 1998.

Before the accumulation of 

8,000 total flight cycles 

or 20,000 total flight 

hours, whichever occurs 

first.

Within 800 flight cycles or 

1,500 flight hours after 

August 26, 2005 (the effective date of AD 2005– 

15–01, Amendment 39– 

14190 (70 FR 42262, 

July 22, 2005)), whichever occurs first.

At intervals not to exceed 

800 flight cycles or 

1,500 flight hours, 

whichever occurs first.

Inspection and modification in accordance with 

Part 2.A. of Lockheed 

TriStar L–1011 Service 

Bulletin 093–53–260, 

Basic Issue, dated May 

15, 1991. 

(14) Change Notification 

093–53–266, CN1, dated 

July 10, 1992.

Within 12 months after August 26, 2005 (the effective date of AD 2005– 

15–01, Amendment 39– 

14190 (70 FR 42262, 

July 22, 2005)).

(None) ............................... At intervals not to exceed 

90 days.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–53–266, Basic 

Issue, dated March 2, 

1992. 

(15) Change Notification 

093–57–058, R5–CN1, 

dated May 3, 1993.

Before the accumulation of 

20,000 total flight cycles 

or 37,000 total flight 

hours, whichever occurs 

first.

Within 1,600 flight cycles 

or 3,000 flight hours 

after August 26, 2005 

(the effective date of AD 

2005–15–01, Amendment 39–14190 (70 FR 

42262, July 22, 2005)), 

whichever occurs first.

At intervals not to exceed 

1,600 flight cycles or 

3,000 flight hours, 

whichever occurs first.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–57–058, Basic 

Issue, dated September 

16, 1975; Revision 1, 

dated December 1, 

1976; Revision 2, dated 

June 30, 1978; Revision 

3, dated October 19, 

1978; or Revision 4, 

dated July 6, 1981, Revision 5, dated June 9, 

1983. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
63280 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—Continued 

Lockheed TriStar L–1011 

Service Bulletin 

Initial compliance time 

(whichever occurs later between the times in ‘‘Inspection 

Threshold’’ and ‘‘Grace Period’’) Repetitive intervals Terminating action 

Inspection threshold Grace period 

(16) Change Notification 

093–57–195, R3–CN1, 

dated August 22, 1995, 

or Lockheed TriStar L– 

1011 Service Bulletin 

093–57–195, Revision 4, 

dated March 17, 2010.

At the applicable time 

specified in paragraph (j) 

of this AD.

At the applicable time 

specified in paragraph (j) 

of this AD.

At the applicable time 

specified in paragraph 

(k) of this AD.

Modification in accordance 

with Lockheed TriStar 

L–1011 Service Bulletin 

093–57–195, Revision 2, 

dated July 27, 1990; Revision 3, dated June 30, 

1992; or Revision 4, 

dated March 17, 2010 

(17) Change Notification 

093–57–213, CN1, dated 

February 20, 1996.

For Model L–1011–385–1, 

L–1011–385–1–14, L– 

1011–385–1–15: Before 

the accumulation of 

15,000 total flight cycles.

For Model L–1011–385–3: 

Before the accumulation 

of 10,000 total flight cycles.

Within 6,450 flight cycles 

or 5 years after August 

26, 2005 (the effective 

date of AD 2005–15–01, 

Amendment 39–14190 

(70 FR 42262, July 22, 

2005)), whichever occurs first.

At intervals not to exceed 

6,450 flight cycles or 5 

years, whichever occurs 

first.

Repair or modification in 

accordance with Lockheed TriStar L–1011 

Service Bulletin 093–57– 

213, Basic Issue, dated 

December 9, 1994. 

(h) Retained Corrective Action With a 

Certain Compliance Method Removed 

This paragraph restates the corrective 

action required by paragraph (b) of AD 2005– 

15–01, Amendment 39–14190 (70 FR 42262, 

July 22, 2005), with certain exceptions. If any 

cracking or corrosion is detected during any 

inspection required by paragraph (g) of this 

AD, prior to further flight, accomplish the 

actions specified in paragraph (h)(1), (h)(2), 

or (h)(3) of this AD. 

(1) Repair in accordance with the 

applicable service bulletin referenced in table 

I or II of Lockheed Tristar L–1011 Service 

Bulletin 093–51–041, Revision 1, dated 

March 3, 2000, or Revision 2, dated March 

30, 2010. 

(2) Accomplish the terminating 

modification in accordance with the 

applicable service bulletin referenced in table 

I or II of Lockheed Tristar L–1011 Service 

Bulletin 093–51–041, Revision 1, dated 

March 3, 2000, or Revision 2, dated March 

30, 2010. 

(3) Repair in accordance with a method 

approved by the Manager, Atlanta Aircraft 

Certification Office (ACO), FAA. Information 

on additional methods of compliance can be 

obtained from the Manager, Atlanta ACO. 

(i) Retained Terminating Action 

This paragraph restates the terminating 

action required by paragraph (c) of AD 2005– 

15–01, Amendment 39–14190 (70 FR 42262, 

July 22, 2005). Within 5 years or 5,000 flight 

cycles after August 26, 2005 (the effective 

date of AD 2005–15–01), whichever occurs 

first, install the terminating modification 

referenced in the applicable service bulletin 

listed in table 1 to paragraph (g) of this AD, 

in accordance with the applicable service 

bulletin. Such installation constitutes 

terminating action for the applicable 

structural inspection required by paragraph 

(g) of this AD. 

(j) Newly Revised Initial Inspection 

Compliance Time for Certain Airplanes 

For airplanes identified in Lockheed 

TriStar L–1011 Service Bulletin 093–57–195, 

Revision 4, dated March 17, 2010: Do the 

initial inspection required by paragraph 

(g)(16) of this AD at the applicable time 

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

AD. 

(1) For airplanes having serial numbers (S/ 

Ns) 1002 through 1109 inclusive: At the 

earlier of the times specified in paragraphs 

(j)(1)(i) and (j)(1)(ii) of this AD. 

(i) Before the accumulation of 20,000 total 

flight cycles, or within 2,200 flight cycles 

after August 26, 2005 (the effective date of 

AD 2005–15–01, Amendment 39–14190 (70 

FR 42262, July 22, 2005)), whichever occurs 

later. 

(ii) Before the accumulation of 15,000 total 

flight cycles, or within 2,200 flight cycles 

after the effective date of this AD, whichever 

occurs later. 

(2) For airplanes having S/Ns 1110 through 

1250 inclusive: At the earlier of the times 

specified in paragraphs (j)(2)(i) and (j)(2)(ii) 

of this AD. 

(i) Before the accumulation of 30,000 total 

flight cycles, or within 2,200 flight cycles 

after August 26, 2005 (the effective date of 

AD 2005–15–01, Amendment 39–14190 (70 

FR 42262, July 22, 2005)), whichever occurs 

later. 

(ii) Before the accumulation of 15,000 total 

flight cycles, or within 2,200 flight cycles 

after the effective date of this AD, whichever 

occurs later. 

(k) Newly Revised Repetitive Intervals for 

Certain Airplanes 

For airplanes identified in paragraph (j) of 

this AD, repeat the inspection required by 

paragraph (j) of this AD thereafter at the 

applicable times specified in paragraph (k)(1) 

or (k)(2) of this AD. 

(1) For airplanes having S/Ns 1002 through 

1156 inclusive: Repeat the inspection at 

intervals not to exceed 2,200 flight cycles. 

(2) For airplanes having S/Ns 1157 through 

1250 inclusive: Repeat the inspection one 

time within 2,200 flight cycles after the most 

recent inspection; and thereafter at intervals 

not to exceed 1,750 flight cycles. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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. 

(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. 

(m) Related Information 

(1) For more information about this AD, 

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– 

5605; email: carl.w.gray@faa.gov. 

(2) 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; telephone 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. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 63281 

Issued in Renton, Washington, on October 

5, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–25463 Filed 10–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1072; Directorate 

Identifier 2012–NM–141–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 adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This proposed AD was 

prompted by reports of two in-service 

incidents where the left main landing 

gear (MLG) failed to extend. This 

proposed AD would require installing 

stopper plates on the aft uplock frames 

in the MLG bay adjacent to the right and 

left MLG uplock assemblies. We are 

proposing this AD to prevent incorrect 

installation of the upper bolt in the MLG 

uplock assembly, which could prevent 

the MLG from extending and adversely 

affect the safe landing of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 30, 

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, 

Que ́bec H4S 1Y9, Canada; telephone 

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, WA. 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; phone: 516–228–7328; 

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–2012–1072; Directorate Identifier 

2012–NM–141–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 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–22, 

dated July 24, 2012 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

There have been two reported in-service 

incidents where the left main landing gear 

(MLG) failed to extend. The investigation 

revealed that in both cases, the uplock 

assembly had been replaced prior to the inservice incidents and the upper bolt of the 

uplock assembly was incorrectly installed. 

The incorrect installation of the upper bolt 

resulted in the uplock assembly pivoting on 

the lower attachment bolt and preventing the 

MLG from extending under normal or 

alternate extension 

The potential for an incorrect installation of 

the upper bolt could occur at both the left 

hand side (LHS) and/or the right hand side 

(RHS) MLG uplock assembly. Failure of the 

MLG to extend could adversely affect the safe 

landing of the aeroplane. 

This [Canadian] AD mandates the installation 

of stopper plates on the aft uplock frames in 

the MLG bay, adjacent to both the RHS and 

LHS MLG uplock assemblies, to prevent an 

incorrect installation of the MLG uplock 

assembly. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 601R–32–109, dated May 29, 

2012. 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 574 products of U.S. 

registry. We also estimate that it would 

take about 5 work-hours per product to 

comply with the 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 

$243,950, or $425 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 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1