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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Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 20523 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 95–20–04 R1, 

Amendment 39–9454 (60 FR 63414, 

December 11, 1995). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

August 8, 2011 (76 FR 48049). That 

NPRM proposed to continue to require 

implementation of a SID program of 

structural inspections to detect fatigue 

cracking, and repair if necessary. That 

NPRM also proposed to add Model L– 

1011–385–3 airplanes to the 

applicability, change certain inspection 

thresholds and intervals for Model L– 

1011–385–1, L–1011–385–1–14, and L– 

1011–385–1–15 airplanes, include three 

additional SSDs for Model L–1011–385– 

3 airplanes, and remove an SSD that has 

been addressed by a different AD action. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal NPRM (76 FR 

48049, August 8, 2011) and the FAA’s 

response to each comment. 

Request To Withdraw NPRM (76 FR 

48049, August 8, 2011) 

An anonymous commenter requested 

that we stop ‘‘regulating job(s) out of 

this country’’ and leave companies 

alone to run their business as they see 

fit. 

We infer the commenter is requesting 

that we withdraw the NPRM (76 FR 

48049, August 8, 2011). We disagree. 

This AD addresses an identified unsafe 

condition. If the structural inspections 

required by this AD are not done, an 

airplane could develop fatigue cracking 

that could compromise the structural 

integrity of the airplane. We have not 

revised this AD in this regard. 

Request To Clarify Reference 

Lockheed Martin requested that we 

clarify the section of the document 

referenced in paragraph (g)(5) of the 

NPRM (76 FR 48049, August 8, 2011) by 

replacing ‘‘Appendix VI’’ with ‘‘Section 

VI., Appendix.’’ The commenter noted 

that there is no Appendix VI in the 

document and that there is a section VI 

titled Appendix. 

We agree, for the reason provided by 

the commenter. We have revised 

paragraph (g)(5) of this AD accordingly. 

Clarification of Repair Service 

Information 

We have added Note 1 following 

paragraph (n)(1) of this AD to clarify 

that guidance on doing repairs in 

accordance with a ‘‘L–1011–385 Series 

Supplemental Inspection Document’’ 

specified in paragraph (n)(1) of this AD 

can be found in the applicable service 

bulletins identified in certain SSDs of 

the ‘‘L–1011–385 Series Supplemental 

Inspection Document.’’ 

Explanation of Changes Made to This 

AD 

We have revised certain headers 

throughout this AD. We have also 

revised the wording in paragraph (g) of 

this AD. These changes have not 

changed the intent of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

48049, August 8, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 48049, 

August 8, 2011). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 26 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product 

Number of 

airplanes 

affected 

Cost for U.S. 

operators 

Incorporate SID into maintenance program [retained actions from AD 95– 

20–04 R1, Amendment 39–9454 (60 

FR 63414, December 11, 1995)].

550 work-hours × 

$85 per hour = 

$46,750.

$0 $46,750 ................... 26 $1,215,500. 

Initial inspections [retained actions from 

AD 95–20–04 R1, Amendment 39– 

9454 (60 FR 63414, December 11, 

1995)].

245 work-hours × 

$85 per hour = 

$20,825.

$0 $20,825 ................... 26 $541,450. 

Repetitive inspections [retained actions 

from AD 95–20–04 R1, Amendment 

39–9454 (60 FR 63414, December 11, 

1995)].

52 work-hours × $85 

per hour = $4,420 

per inspection 

cycle.

$0 $4,420 per inspection cycle.26 $114,920 per inspection cycle. 

Incorporate SID into maintenance program [new action for Model L–1011– 

385–3 airplanes].

1 work-hour × 85 = 

$85.

$0 $85 .......................... 2 $170. 

Initial inspections [new action for Model 

L–1011–385–3 airplanes].

48 work-hours × $85 

per hour = $4,080.

$0 $4,080 ..................... 2 $8,160. 

Repetitive inspections [new action for 

Model L–1011–385–3 airplanes].

44 work-hours × $85 

per hour = $3,740 

per inspection 

cycle.

$0 $3,740 per inspection cycle.2 $7,480 per inspection cycle. 

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, 


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20524 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 

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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

95–20–04 R1, Amendment 39–9454 (60 

FR 63414, December 11, 1995), and 

adding the following new AD: 

2012–05–06 Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company: 

Amendment 39–16978; Docket No. 

FAA–2011–0723; Directorate Identifier 

2010–NM–080–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 10, 2012. 

(b) Affected ADs 

This AD supersedes AD 95–20–04 R1, 

Amendment 39–9454 (60 FR 63414, 

December 11, 1995). 

(c) Applicability 

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 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the manufacturer of usage and flight data that 

provided additional information about 

certain structurally significant details (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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Maintenance Program Revision 

This maintenance program revision is 

retained from AD 95–20–04 R1, Amendment 

39–9454 (60 FR 63414, December 11, 1995): 

For Model L–1011–385–1, L–1011–385–1–14, 

and L–1011–385–1–15 airplanes: Within 12 

months after November 2, 1995 (the effective 

date of AD 95–20–04 R1, Amendment 39– 

9454 (60 FR 63414, December 11, 1995)), 

incorporate a revision into the maintenance 

inspection program which provides for 

inspection(s) of the structurally significant 

details (SSD) defined in Lockheed Document 

Number LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

January 1994. Doing the revision required by 

paragraph (h) of this AD terminates the 

requirement to revise the maintenance 

inspections program specified in this 

paragraph. Doing the inspections required by 

paragraph (i) of this AD terminates the 

corresponding inspection requirements of 

this paragraph. 

(1) The initial inspection for each SSD 

must be performed at the later of the times 

specified in paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD. 

(i) Within one repeat interval measured 

from November 2, 1996 (12 months after 

November 2, 1995). 

(ii) Prior to the threshold specified in 

Lockheed Document Number LG92ER0060, 

‘‘L–1011–385 Series Supplemental 

Inspection Document,’’ revised January 1994, 

for that SSD. 

(2) A 10 percent deviation from the 

repetitive interval specified in Lockheed 

Document Number LG92ER0060, ‘‘L–1011– 

385 Series Supplemental Inspection 

Document,’’ revised January 1994, for that 

SSD is acceptable to allow for planning and 

scheduling time. 

(3) If Lockheed Document Number 

LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

January 1994, specifies that inspection of any 

SSD be performed at every ‘‘C’’ check, those 

inspections must be performed at intervals 

not to exceed 5,000 hours time-in-service or 

2,500 flight cycles, whichever occurs earlier. 

(4) If Lockheed Document Number 

LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

January 1994, specifies either the initial 

inspection or the repetitive inspection 

intervals for any SSD in terms of flight hours 

or flight cycles, the inspection shall be 

performed prior to the earlier of the terms 

(whichever occurs first on the airplane: either 

accumulated number of flight hours, or 

accumulated number of flight cycles). 

(5) The non-destructive inspection 

techniques referenced in Section VI., 

‘‘Appendix,’’ of Lockheed Document Number 

LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

January 1994, provide acceptable methods for 

accomplishing the inspections required by 

paragraph (g) of this AD. 

(h) New Requirements of This AD: 

Maintenance Program Revision 

For all airplanes: Within 12 months after 

the effective date of this AD, incorporate a 

revision into the maintenance inspection 

program which provides for inspection(s) of 

the SSDs defined in Lockheed Document 

Number LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009. Doing this revision terminates 

the requirement to revise the maintenance 

inspection program as specified in paragraph 

(g) of this AD. 

(i) New Requirement of This AD: Threshold 

and Intervals 

For all airplanes: Do all applicable 

inspections specified in Lockheed Document 

Number LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009. Do the initial inspection or next 

repetitive inspection at the applicable time 

specified in paragraphs (i)(1) and (i)(2) of this 

AD, except as provided by paragraphs (j), (k), 

and (l) of this AD. Repeat the inspections 

thereafter in accordance with the intervals 

and actions specified in Lockheed Document 

Number LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009, except as provided by paragraphs 

(j), (k), and (l) of this AD. The nondestructive inspection techniques referenced 

in Lockheed Document Number 

LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009, provide acceptable methods for 

accomplishing the inspections required by 

this AD. Doing the inspections required by 

this paragraph of this AD terminates the 

corresponding inspection requirements of 

paragraph (g) of this AD. 

(1) For Model L–1011–385–3 airplanes; 

and for Model L–1011–385–1, L–1011–385– 

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

which the initial inspection required by 

paragraph (g) of this AD has not been 


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Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 20525 

accomplished before the effective date of this 

AD: Do the initial inspection at the later of 

the times specified in paragraphs (i)(1)(i) and 

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

(i) Within one repeat interval measured 

from a date 12 months after the effective date 

of this AD. 

(ii) Before the threshold specified for that 

SSD in Lockheed Document Number 

LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009. 

(2) For Model L–1011–385–1, L–1011–385– 

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

which the initial inspection required by 

paragraph (g) of this AD has been 

accomplished before the effective date of this 

AD: Do the next repetitive inspection at the 

earlier of the times specified in paragraphs 

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

(i) Within the next repetitive inspection 

interval specified in Lockheed Document 

Number LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

January 1994, for that SSD. 

(ii) Within one repeat interval measured 

from a date 12 months after the effective date 

of this AD; or within the next repetitive 

interval specified in Lockheed Document 

Number LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009, for that SSD; whichever occurs 

later. 

(j) Exception to Intervals—10 Percent 

Deviation Allowed 

For all airplanes: A 10 percent deviation 

from the repetitive interval specified in 

Lockheed Document Number LG92ER0060, 

‘‘L–1011–385 Series Supplemental 

Inspection Document,’’ revised April 2009, 

for that SSD is acceptable to allow for 

planning and scheduling time. 

(k) Exception to Intervals Specifying ‘‘C’’ 

Check 

For all airplanes: Where Lockheed 

Document Number LG92ER0060, ‘‘L–1011– 

385 Series Supplemental Inspection 

Document,’’ revised April 2009, specifies that 

inspection of any SSD be performed at every 

‘‘C’’ check, those inspections must be 

performed at intervals not to exceed 5,000 

flight hours or 2,500 flight cycles, whichever 

occurs earlier. 

(l) Exceptions to Threshold and Intervals 

For all airplanes: Where Lockheed 

Document Number LG92ER0060, ‘‘L–1011– 

385 Series Supplemental Inspection 

Document,’’ revised April 2009, specifies 

either the initial inspection or the repetitive 

inspection intervals for any SSD in terms of 

flight hours or flight cycles, the inspection 

must be performed prior to the earlier of the 

terms (whichever occurs first on the airplane: 

either accumulated number of flight hours, or 

accumulated number of flight cycles). 

(m) Exception to Inspection Procedure 

For all airplanes: There should be no repair 

or modification work done in the inspection 

area before the initial inspections required by 

paragraph (i) of this AD; any changes in the 

inspection area could affect the inspection 

procedure. 

(n) New Requirements of This AD: Repair 

For all airplanes: If any cracking is found 

in any SSD during any inspection required 

by this AD, prior to further flight, repair in 

accordance with paragraph (n)(1), (n)(2), or 

(n)(3) of this AD: 

(1) In accordance with the Lockheed 

Document Number LG92ER0060, ‘‘L–1011– 

385 Series Supplemental Inspection 

Document,’’ revised January 1994; or revised 

April 2009. After doing the revision required 

by paragraph (h) of this AD, repair in 

accordance with Lockheed Document 

Number LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009. 

Note 1 to paragraph (n)(1) of this AD: 

Guidance on doing repairs in accordance 

with a ‘‘L–1011–385 Series Supplemental 

Inspection Document’’ specified in paragraph 

(n)(1) of this AD can be found in the 

applicable service bulletins identified in 

certain SSDs of the ‘‘L–1011–385 Series 

Supplemental Inspection Document’’ 

specified in paragraph (n)(1) of this AD. 

(2) In accordance with Lockheed L–1011 

Structural Repair Manual, Revision 80, dated 

December 15, 2009. 

(3) In accordance with a method approved 

by the Manager, Atlanta Aircraft Certification 

Office (ACO), FAA. 

(o) New Requirements of This AD: Reporting 

For all airplanes: At the later of the times 

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

this AD, submit a report of the results 

(positive or negative) of the inspection(s) to 

Lockheed in accordance with Section V., 

Data Reporting System (DRS), of the 

applicable Lockheed Document specified in 

paragraph (o)(1) of this AD. Under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) Within 30 days after returning the 

airplane to service, subsequent to 

accomplishment of the inspection(s) 

specified in Lockheed Document Number 

LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

January 1994; or Lockheed Document 

Number LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009. 

(2) Within 30 days after the effective date 

of this AD. 

(p) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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. 

(r) Related Information 

For more information about this AD, 

contact Carl Gray, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, Atlanta 

ACO, 1701 Columbia Avenue, College Park, 

Georgia 30337; phone: 404–474–5554; fax: 

404–474–5606; email: Carl.W.Gray@faa.gov. 

(s) Material Incorporated by Reference 

(1) 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 on 

the date specified. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on May 10, 2012. 

(i) Lockheed Document Number 

LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

April 2009. 

(ii) Lockheed L–1011 Structural Repair 

Manual, Revision 80, dated December 15, 

2009, which contains the following errors: 

(A) Page 13/14 of Section 51–10–06, pages 

1 through 10 of the Table of Contents for 

Chapter 54, and page 809/810 of Section 55– 

35–00 show a page date of ‘‘Date 15XX;’’ 

these pages should be dated December 15, 

2009. 

(B) The List of Effective Pages for Chapter 

51 identifies incorrect dates for pages 3 and 

4 of the Table of Contents for Chapter 51; the 

correct date of those pages is March 15, 1999. 

(C) Page 7 of the List of Effective Pages for 

Chapter 53 does not list a configuration 

number for page 20 of Section 53–21–00; that 

page should be identified as configuration 2. 

(D) The List of Effective Pages for Chapter 

53 identifies incorrect dates for pages 3 and 

5 of Section 53–14–00 (Configuration 2); the 

correct dates are September 15, 1995, for 

page 3, and March 15, 1994, for page 5. 

(E) The List of Effective Pages for Chapter 

53 identifies an incorrect date for page 4 of 

Section 53–15–00; the correct date for that 

page is September 15, 1981. 


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20526 Federal Register / Vol. 77, No. 66 / Thursday, April 5, 2012 / Rules and Regulations 

(F) The List of Effective Pages for Chapter 

54 identifies an incorrect date for page 1 of 

Section 54–23–00; the correct date for that 

page is May 15, 1986. 

(G) The List of Effective Pages for Chapter 

54 identifies an incorrect date for page 4 of 

Section 54–32–00; the correct date for that 

page is March 15, 1992. 

(H) The List of Effective Pages for Chapter 

57 identifies an incorrect date for page 13 of 

Section 57–00–00; the correct date for that 

page is April 15, 2005. 

(I) The List of Effective Pages for Chapter 

57 identifies an incorrect date for pages 16 

and 18 of Section 57–12–00; the correct date 

for those pages is March 15, 1983. 

(J) The List of Effective Pages for Chapter 

57 identifies an incorrect date for pages 801, 

802, and 805/806 of Section 57–13–00; the 

correct date for those pages is December 15, 

2009. 

(K) The List of Effective Pages for Chapter 

57 identifies an incorrect date for pages 810 

through 819 of Section 57–51–00; the correct 

date for those pages is December 15, 2009. 

(L) The List of Effective Pages for Chapter 

57 identifies an incorrect date for page 4 of 

Section 57–52–00; the correct date for that 

page is December 15, 2009. 

(M) Page 25, dated March 15, 1983, and 

page 26, dated May 15, 1986, of Section 57– 

12–00 were inadvertently omitted from the 

List of Effective Pages for Chapter 57. 

(4) The following service information was 

approved for IBR November 2, 1995 (60 FR 

51713, October 3, 1995). 

(i) Lockheed Document Number 

LG92ER0060, ‘‘L–1011–385 Series 

Supplemental Inspection Document,’’ revised 

January 1994. 

(5) For service information identified in 

this AD, contact Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company, L1011 Technical Support Center, 

Dept. 6A4M, Zone 0579, 86 South Cobb 

Drive, Marietta, Georgia 30063–0579; 

telephone 770–494–5444; fax 770–494–5445; 

email L1011.support@lmco.com; Internet 

http://www.lockheedmartin.com/ams/tools/ 

TechPubs.html. 

(6) 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. 

(7) 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, WA, on March 1, 2012. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–8040 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–2011–1318; Directorate 

Identifier 2010–NM–274–AD; Amendment 

39–17009; AD 2012–07–03] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all 328 Support Services GmbH (Type 

Certificate previously held by AvCraft 

Aerospace GmbH; Fairchild Dornier 

GmbH; Dornier Luftfahrt GmbH) Model 

328–100 and –300 airplanes. That AD 

currently requires performing a detailed 

visual inspection of the cockpit door 

locking device and the surrounding area 

for proper installation, and corrective 

action if necessary. This new AD 

requires removing or replacing the 

locking device of the cockpit door; 

performing operational tests, and repair 

if necessary; and, for certain airplanes, 

installing gap filler parts. This AD was 

prompted by a report that a right-hand 

power lever jammed in flight-idle 

position during the landing roll-out, and 

the airplane was stopped by excessive 

braking. We are issuing this AD to 

detect and correct interference with the 

engine and flight control cables, which 

could result in reduced controllability 

of the airplane. 

DATES: This AD becomes effective May 

10, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 10, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 20, 2009 (74 FR 

53151, October 16, 2009). 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

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 December 12, 2011 (76 FR 

77159), and proposed to supersede AD 

2009–21–06, Amendment 39–16043 (74 

FR 53151, October 16, 2009). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

The MCAI states: 

An incident has been reported with a 

Dornier 328–100 aeroplane, where the righthand (RH) power lever jammed in flight-idle 

position during the landing roll-out. The 

aeroplane was stopped by excessive braking. 

The reason for the jamming was that the 

cockpit door locking device Part Number (P/ 

N) 001A252A3914012 had fallen off the RH 

cockpit wall, blocking the RH power/ 

condition lever pulley/cable cluster below 

the door. Although the affected aeroplane 

had been modified, the technical 

investigation showed that a loose Cockpit 

Door Locking device could also occur on 

328–100 and 328–300 aeroplanes with a 

standard installation. 

This condition, if not corrected, could 

cause interference with the engine and/or 

flight control cables, possibly resulting in 

reduced control of the aeroplane. 

To address that unsafe condition, EASA 

issued AD 2009–0082 [which corresponds to 

FAA AD 2009–21–06, Amendment 39–16043 

(74 FR 53151, October 16, 2009)] as an 

interim solution, to require a one-time 

inspection of the cockpit door locking device 

and the surrounding area and the reporting 

of all findings to the TC [type certificate] 

holder. 

Since that AD was issued, the TC holder 

has developed an improved cockpit door 

locking device, P/N 001A252A3914016. 

Consequently, this [EASA] AD retains the 

requirements of [EASA] AD 2009–0082, 

which is superseded, and requires the 

replacement of the current P/N 

001A252A3914012 with new designed P/N 

001A252A3914016 cockpit door locking 

device, or the removal of the cockpit door 

locking device P/N 001A252A3914012 and 

the installation of a gap filler, as applicable 

to aeroplane configuration. 

The required actions include performing 

operational tests, and repair if 

necessary. 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 

received no comments on the NPRM (76 

FR 77159, December 12, 2011) or on the 

determination of the cost to the public. 


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