59640 Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0650; Directorate 

Identifier 2014–NM–162–AD; Amendment 

39–17974; AD 2014–20–01] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B16 

(CL–601–3A, CL–601–3R, and CL–604 

Variants) airplanes. This AD requires 

repetitive inspections for any fuel leak 

in the right-hand landing lights 

compartment, and related investigative 

and corrective actions if necessary. This 

AD also provides for an optional 

replacement of the connector of the fuel 

boost pump canister of the auxiliary 

power unit (APU), which terminates the 

repetitive inspections. This AD was 

prompted by a report of fuel leaks in the 

connector cavity of the APU fuel boost 

pump canister and at the electrical 

conduit connection of the APU fuel 

boost pump in the right-hand landing 

lights compartment. We are issuing this 

AD to detect and correct fuel leaks in 

the right-hand landing lights 

compartment, which, in combination 

with the heat generated by the taxi 

lights and landing lights on the ground 

reaching the auto-ignition temperature 

of the fuel, could result in ignition of 

any fuel or fumes present in the righthand landing lights compartment. 

DATES: This AD becomes effective 

October 20, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 20, 2014. 

We must receive comments on this 

AD by November 17, 2014. 

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: 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 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. You may view 

this 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 by searching for 

and locating Docket No. FAA–2014– 

0650; 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 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: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Services Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7301; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–21, 

dated July 10, 2014 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B16 (CL–601–3A, CL–601–3R, and 

CL–604 Variants) airplanes. The MCAI 

states: 

Bombardier Inc. has discovered fuel 

leakage in the auxiliary power unit (APU) 

fuel Boost Pump (BP) canister connector 

cavity. On some of those aeroplanes, leakage 

was also noticed at the APU fuel BP electrical 

conduit connection in the right hand landing 

light compartment. The root cause of the 

subject fuel leak is identified to be the 

improper length of the female connector 

keyway located in the fuel BP canister, 

causing a shift of the electrical harness and 

its seals. 

Available data indicates that on a hot day, 

due to the heat generated by the taxi light 

and/or landing lights on the ground, 

temperature in the landing light 

compartment can reach the fuel auto ignition 

temperature. Therefore, presence of any fuel 

in the right hand landing light compartment 

is considered to be a safety hazard [fuel or 

fumes present in the right-hand landing 

lights compartment might ignite] that 

warrants mitigating action. 

In order to help mitigate the potential 

safety hazard precipitated by any fuel leakage 

in the right hand landing light compartment, 

Bombardier Inc., has revised the Aircraft 

Flight Manual (AFM) through Temporary 

Revisions (TRs) 604/38 and 605/20 dated 16 

June 2014 to restrict the operation of Taxi 

and Landing lights on the ground. Transport 

Canada issued Emergency [Canadian] AD 

CF–2014–17 [(http://wwwapps3.tc.gc.ca/SafSec-Sur/2/cawis-swimn/

attachment.asp?aiid=CF-2014- 

17&revid=0&cntr=CF&file=CFCF-2014- 

17.pdf&type=PDE), which corresponds to 

FAA AD 2014–15–17, Amendment 39–17919 

(79 FR 44268, July 31, 2014)] to mandate 

incorporation of the above AFM TRs. 

To address the root cause of the subject 

fuel leakage from the APU fuel boost pump 

canister wiring conduit, Bombardier Inc. 

issued Alert Service Bulletin (ASB) A605– 

28–008 that requires periodic [repetitive 

general visual] inspection[s] for fuel leaks 

and [applicable related investigative and 

corrective actions and] eventual the 

replacement of the discrepant fuel BP 

canister connectors [including related 

investigative and corrective actions] on 

affected aeroplanes. The ASB has been 

revised to include an additional inspection of 

the new connector wiring for damage and 

this [Canadian] AD is issued to mandate the 

compliance with ASB A605–28–008 Revision 

2 requirements. 

Related investigative actions include 

doing a general visual inspection for any 

fuel leak in the wiring conduit of the 

APU fuel boost pump in the right-hand 

landing lights compartment; a detailed 

inspection for damage of the O-rings of 

the fuel pump cartridge; and a detailed 

inspection of the wires under the wiring 

insulation sleeve of the new connector 

for cuts. Corrective actions include 

installing new packings on the APU fuel 

pump cartridge, replacing the connector 

on the APU fuel pump canister, and 

replacing wiring and O-rings if certain 

conditions are found. You may examine 

the MCAI on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0650. 

Relevant Service Information 

Bombardier, Inc. has issued 

Bombardier Alert Service Bulletin 

A605–28–008, Revision 02, dated July 9, 

2014. The actions described in this 

service information are intended to 


rmajette on DSK2TPTVN1PROD with RULES
Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations 59641 

correct the unsafe condition identified 

in the MCAI. 

Other Relevant Rulemaking 

On July 24, 2014, the FAA issued AD 

2014–15–17, Amendment 39–17919 (79 

FR 44268, July 31, 2014), for certain 

Bombardier, Inc. Model CL–600–2B16 

(CL–604 Variant) airplanes. AD 2014– 

15–17 requires revising the airplane 

flight manual to incorporate temporary 

revisions that introduce additional 

limitations for operation of taxi and 

landing lights. AD 2014–15–17 requires 

revising the airplane flight manual only 

for Bombardier, Inc. Model CL–600– 

2B16 (CL–604 Variant) airplanes, serial 

numbers 5301 through 5665 inclusive, 

and 5701 and subsequent. This AD 

requires repetitive inspections for any 

fuel leak in the right-hand landing lights 

compartment, and related investigative 

and corrective actions if necessary, for 

Bombardier, Inc. Model CL–600–2B16 

(CL–601–3A, CL–601–3R, and CL–604 

Variants) airplanes, serial numbers 

5906, 5910, 5912, 5917, 5919 through 

5932 inclusive, 5934, 5935, 5939, 5940, 

5942, and 5948. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

The MCAI and Bombardier Alert 

Service Bulletin A605–28–008, Revision 

02, dated July 9, 2014, do not specify 

corrective actions if any cut is found on 

the wires or if any damage is found on 

the O-rings during certain related 

investigative actions. This AD requires 

that a replacement be done using a 

method approved by the FAA, TCCA, or 

Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because fuel leaks in the right-hand 

landing lights compartment, in 

combination with the heat generated by 

the taxi lights and landing lights on the 

ground reaching the auto-ignition 

temperature of the fuel, could result in 

ignition of any fuel or fumes present in 

the right-hand landing lights 

compartment. Therefore, we determined 

that notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2014–0650; 

Directorate Identifier 2014–NM–162– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Interim Action 

This AD is considered to be interim 

action. We are currently considering 

requiring a replacement of the connector 

of the fuel boost pump canister of the 

APU, and applicable related 

investigative and corrective actions, 

which will constitute terminating action 

for the repetitive inspections required 

by this AD action. However, the 

planned compliance time for the 

replacement would allow enough time 

to provide notice and opportunity for 

prior public comment on the merits of 

the replacement and applicable related 

investigative and corrective actions. 

Costs of Compliance 

We estimate that this AD affects 92 

airplanes of U.S. registry. 

We also estimate that it will take 

about 2 work-hours 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 on U.S. 

operators to be $15,640, or $170 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 22 work-hours and require parts 

costing $0, for a cost of $1,870 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 that this AD: 

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. 


rmajette on DSK2TPTVN1PROD with RULES
59642 Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations 

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 airworthiness 

directive (AD): 

2014–20–01 Bombardier, Inc.: Amendment 

39–17974. Docket No. FAA–2014–0650; 

Directorate Identifier 2014–NM–162–AD. 

(a) Effective Date 

This AD becomes effective October 20, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B16 (CL–601–3A, CL–601–3R, and 

CL–604 Variants) airplanes, certificated in 

any category, serial numbers 5906, 5910, 

5912, 5917, 5919 through 5932 inclusive, 

5934, 5935, 5939, 5940, 5942, and 5948. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by a report of fuel 

leaks in the auxiliary power unit (APU) fuel 

boost pump canister connector cavity and in 

the right-hand landing lights compartment 

from the APU fuel boost pump electrical 

conduit connection. We are issuing this AD 

to detect and correct fuel leaks in the righthand landing lights compartment, which, in 

combination with the heat generated by the 

taxi lights and landing lights on the ground 

reaching the auto-ignition temperature of the 

fuel, could result in ignition of any fuel or 

fumes present in the right-hand landing 

lights compartment. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections for Fuel Leaks 

Within 25 flight hours after the effective 

date of this AD: Do a general visual 

inspection for any fuel leak in the right-hand 

landing lights compartment, and do all 

applicable related investigative and 

corrective actions, in accordance with Part A 

of the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A605–28– 

008, Revision 02, dated July 9, 2014, except 

as required by paragraph (h) of this AD. Do 

all applicable related investigative and 

corrective actions before further flight. 

Repeat the inspection thereafter at intervals 

not to exceed 8 flight hours until the 

replacement specified in paragraph (i) of this 

AD has been accomplished. 

(h) Corrective Action if Fuel Leak Is Found 

During Related Investigative Actions 

If any fuel leak is found during the related 

investigative actions required by paragraph 

(g) of this AD: Before further flight, do the 

terminating action specified in paragraph (i) 

of this AD, or repair using a method 

approved by the Manager, New York Aircraft 

Certification Office (ACO), ANE–170, Engine 

and Propeller Directorate, FAA; or Transport 

Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). 

(i) Optional Terminating Action— 

Replacement 

Replacing the connector of the fuel boost 

pump canister of the APU and doing all 

applicable related investigative actions, in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A605–28–008, 

Revision 02, dated July 9, 2014, terminates 

the actions required by paragraph (g) of this 

AD provided that the following actions are 

done, as applicable. 

(1) If any damage (cuts) is found on the 

wires, before further flight, replace the wire 

with a new wire identified in kit 605K28– 

008A, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A605–28–008, 

Revision 02, dated July 9, 2014. 

(2) If any damage is found on the O-rings, 

before further flight, replace the O-ring with 

a new O-ring, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A605–28–008, 

Revision 02, dated July 9, 2014. 

(3) If any fuel leak is found, before further 

flight, repair using a method approved by the 

Manager, New York ACO, ANE–170, Engine 

and Propeller Directorate, FAA; or TCCA; or 

Bombardier, Inc.’s TCCA DAO. 

(j) Inspection of Connector Wiring 

For airplanes having new connectors 

installed in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A605–28–008, dated 

April 21, 2014: Within 6 months or 150 flight 

hours after the effective date of this AD, 

whichever occurs first, do a detailed 

inspection for damage (cuts) of the connector 

wiring, in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A605–28–008, 

Revision 02, dated July 9, 2014. If any 

damage (cuts) is found on the wires, before 

further flight, replace the wire with a new 

wire identified in kit 605K28–008A, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A605–28–008, Revision 02, dated 

July 9, 2014. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (i) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Alert 

Service Bulletin A605–28–008, Revision 01, 

dated May 28, 2014, which is not 

incorporated by reference in this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA DAO. If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–21, dated 

July 10, 2014, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0650. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Alert Service Bulletin 

A605–28–008, Revision 02, dated July 9, 

2014. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 


rmajette on DSK2TPTVN1PROD with RULES
Federal Register / Vol. 79, No. 192 / Friday, October 3, 2014 / Rules and Regulations 59643 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 19, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–23145 Filed 10–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0290; Directorate 

Identifier 2012–NM–210–AD; Amendment 

39–17981; AD 2014–20–08] 

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 adopting a new 

airworthiness directive (AD) for certain 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model L– 

1011 series airplanes. This AD was 

prompted by reports of cracked rib cap 

castellations. This AD requires 

repetitive inspections for castellation 

and skin clips cracked or damaged 

between stringers and cracked stringer 

clips of the wing box pylon back-up 

structure, and front spar to rear spar; 

repetitive inspections for cracking, 

damage, or failure of the pylon back-up 

torque box structure; repetitive 

inspections for cracking or damage of 

the wing box external areas at the drag 

brace aft wing fitting; repetitive 

inspections of the outer surface of the 

wing upper and lower skins for cracks 

or damage along the rib attachment at 

the fastener holes and between the two 

rows of attachment; and corrective 

actions if necessary. We are issuing this 

AD to detect and correct cracked or 

damaged rib cap castellations, which 

could degrade the structural capabilities 

of the airplane. 

DATES: This AD is effective November 7, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 7, 2014. 

ADDRESSES: 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, 

GA 30063–0579; telephone 770–494– 

5444; fax 770–494–5445; email 

L1011.support@lmco.com; Internet 

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

tools/TechPubs.html. You may view this 

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 by searching for 

and locating Docket No. FAA–2014– 

0290; 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 

Docket 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, GA 

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

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

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Lockheed Martin 

Corporation/Lockheed Martin 

Aeronautics Company Model L–1011 

series airplanes. The NPRM published 

in the Federal Register on May 29, 2014 

(79 FR 30748). The NPRM was 

prompted by reports of cracked rib cap 

castellations. The NPRM proposed to 

require repetitive inspections for 

castellation and skin clips cracked or 

damaged between stringers and cracked 

stringer clips of the wing box pylon 

back-up structure, and front spar to rear 

spar; repetitive inspections for cracking, 

damage, or failure of the pylon back-up 

torque box structure; repetitive 

inspections for cracking or damage of 

the wing box external areas at the drag 

brace aft wing fitting; repetitive 

inspections of the outer surface of the 

wing upper and lower skins for cracks 

or damage along the rib attachment at 

the fastener holes and between the two 

rows of attachment; and corrective 

actions if necessary. We are issuing this 

AD to detect and correct cracked or 

damaged rib cap castellations, which 

could degrade the structural capabilities 

of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 30748, May 29, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

30748, May 29, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 30748, 

May 29, 2014). 

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 Cost on U.S. operators 

Inspections ........ 41 work-hours × $85 per hour = $3,485 per 

inspection cycle.

$0 $3,485 per inspection cycle .. $90,610 per inspection cycle. 


rmajette on DSK2TPTVN1PROD with RULES