13926 Federal Register / Vol. 76, No. 50 / Tuesday, March 15, 2011 / Proposed Rules 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 30 days after the effective date 

of this AD, revise the maintenance program, 

to incorporate the limitation for reduced 

maximum time limit between overhauls 

defined below. This may be done by inserting 

a copy of this AD into the limitations section 

(Chapter 5–40–00) of Dassault Falcon 7X 

Maintenance Manual DGT 107838, as revised 

by Temporary Revision TR–02, dated 

February 19, 2008. 

MPD task Title Max time limit 

24–31–01–350–801 ........................................... Restoration of the DC generators (bearing) .... 650 FH (instead of 1,000 FH). 

Note 2: When a statement identical to that 

in paragraph (g) of this AD has been included 

in the general revisions of the maintenance 

manual, the general revisions may be 

inserted into the maintenance manual and 

the copy of this AD may be removed from the 

maintenance manual provided the relevant 

information in the general revision is 

identical to that in paragraph (g) of this AD. 

(h) For the maintenance planning 

document (MPD) task identified in paragraph 

(g) of this AD, the initial compliance time is 

the later of the times in paragraphs (h)(1), 

(h)(2), and (h)(3) of this AD. 

(1) Prior to the accumulation of 650 flight 

hours on the DC generators (bearings). 

(2) Within 650 flight hours after the last 

accomplishment of the restoration of the DC 

generators (bearing) specified in MPD Task 

24–31–01–350–801. 

(3) Within 12 flight hours after the effective 

date of this AD. 

No Alternative Actions or Intervals 

(i) After accomplishing the revision 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections), or 

intervals may be used unless the actions or 

intervals are approved as an AMOC in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: 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. 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. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2009–0254, dated December 1, 

2009, for related information. 

Issued in Renton, Washington, on March 8, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–5899 Filed 3–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0221; Directorate 

Identifier 2010–NM–120–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model DC–8–11, DC–8–12, 

DC–8–21, DC–8–31, DC–8–32, DC–8– 

33, DC–8–41, DC–8–42, and DC–8–43 

Airplanes; DC–8–50 Series Airplanes; 

DC–8F–54 and DC–8F–55 Airplanes; 

DC–8–60 Series Airplanes; DC–8–60F 

Series Airplanes; DC–8–70 Series 

Airplanes; and DC–8–70F Series 

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 

Model DC–8–11, DC–8–12, DC–8–21, 

DC–8–31, DC–8–32, DC–8–33, DC–8–41, 

DC–8–42, and DC–8–43 airplanes, DC– 

8–50 series airplanes, DC–8F–54 and 

DC–8F–55 airplanes, DC–8–60 series 

airplanes, DC–8–60F series airplanes, 

DC–8–70 series airplanes, and DC–8– 

70F series airplanes. This proposed AD 

would require repetitive high frequency 

eddy current or repetitive low frequency 

eddy current inspections for cracks on 

the area around certain fasteners of the 

access opening doubler on the left and 

right wing center spar lower cap, and 

repair, if necessary. This proposed AD 

results from reports that cracks in the 

center spar lower cap and, in some 

cases, the web of the spar, have been 

found at stations Xrs=168.00, 

Xrs=251.00, and Xrs=358.00. We are 

proposing this AD to detect and correct 

cracks in the area around certain 

fasteners of the access opening doubler 

on the left and right wing center spar 

lower cap, which could compromise the 

structural integrity of the wing 

structure. 

DATES: We must receive comments on 

this proposed AD by April 29, 2011. 

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 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

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Federal Register / Vol. 76, No. 50 / Tuesday, March 15, 2011 / Proposed Rules 13927 

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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Dara 

Albouyeh, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5222; fax (562) 

627–5210. 

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–2011–0221; Directorate Identifier 

2010–NM–120–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We received reports that cracks in the 

center spar lower cap and, in some 

cases, the web of the spar, have been 

found at stations Xrs=168.00, 

Xrs=251.00, and Xrs=358.00. These 

cracks originate in the most inboard 

fastener hole of the access opening 

doublers. A total of 12 cracks have been 

found in airplanes having accumulated 

between 26,121 and 50,136 total flight 

cycles. The cracks appear to be 

consistent with fatigue cracks. Such 

cracking in the area around certain 

fasteners of the access opening doubler 

on the left and right wing center spar 

lower cap, if not detected and corrected, 

could compromise the structural 

integrity of the wing structure. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin DC8–57A103, dated 

May 5, 2010. This service bulletin 

describes procedures for repetitive high 

frequency eddy current (HFEC) 

inspections or low frequency eddy 

current (LFEC) inspections for cracks on 

the area around certain fasteners of the 

left and right wing center spar lower cap 

at stations Xrs=168.00, Xrs=251.00, and 

Xrs=358.00, and repair if necessary. 

This service bulletin also describes 

procedures for repetitive (post-repair) 

inspections for cracking of the repaired 

area, using the inspection defined in 

Method 101 of Section 57–10–06, or 

Method 101 or 104 of Section 57–10–16, 

of the McDonnell Douglas DC–8 

Supplemental Inspection Document 

(SID), Report L26–011, Volume II, 

Revision 8, dated January 2005, as 

applicable. 

For airplanes on which no cracking is 

found, the repetitive interval is either 

1,750 flight cycles or 6,000 flight cycles, 

depending on the inspection type. 

For airplanes on which cracking is 

found, the repetitive interval for nonrepaired areas is either 1,750 flight 

cycles or 6,000 flight cycles, depending 

on the inspection type. 

For airplanes on which cracking is 

found, the compliance time for the 

initial post-repair inspection is between 

7,600 flight cycles and 43,000 flight 

cycles after doing the repair, depending 

on the configuration and inspection 

type. The repetitive interval is between 

1,400 flight cycles and 5,300 flight 

cycles, depending on the configuration 

and inspection type. 

Other Relevant Rulemaking 

This proposed AD will affect the 

inspections, corrective actions, and 

reports required by AD 2008–25–05, 

Amendment 39–15763 (73 FR 78936, 

December 24, 2008), for Principal 

Structural Elements (PSE) 57.08.013/– 

014 and 57.08.035/–036 of the DC–8 

SID. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all 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 require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin DC8– 

57A103, dated May 5, 2010, does not 

specify a corrective action if cracking is 

found during the inspections of the 

repaired area. If cracking is found 

during the inspections of the repaired 

area, this proposed AD would require 

repairing those conditions in one of the 

following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 41 airplanes of U.S. 

registry. We also estimate that it would 

take 12 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this proposed AD to the U.S. 

operators to be $41,820, or $1,020 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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. 

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13928 Federal Register / Vol. 76, No. 50 / Tuesday, March 15, 2011 / Proposed Rules 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2011–0221; Directorate Identifier 2010– 

NM–120–AD. 

Comments Due Date 

(a) We must receive comments by April 29, 

2011. 

Affected ADs 

(b) This AD affects certain requirements of 

AD 2008–25–05, Amendment 39–15763. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model DC–8–11, DC–8–12, DC–8– 

21, DC–8–31, DC–8–32, DC–8–33, DC–8–41, 

DC–8–42, DC–8–43, DC–8–51, DC–8–52, DC– 

8–53, DC–8–55, DC–8F–54, DC–8F–55, DC– 

8–61, DC–8–62, DC–8–63, DC–8–61F, DC–8– 

62F, DC–8–63F, DC–8–71, DC–8–72, DC–8– 

73, DC–8–71F, DC–8–72F, and DC–8–73F 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports that cracks 

in the center spar lower cap and, in some 

cases, the web of the spar, have been found 

at stations Xrs=168.00, Xrs=251.00, and 

Xrs=358.00. The Federal Aviation 

Administration is issuing this AD to detect 

and correct cracks in the area around certain 

fasteners of the access opening doubler on 

the left and right wing center spar lower cap, 

which could compromise the structural 

integrity of the wing structure. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection 

(g) Before the accumulation of 20,000 total 

flight cycles, or within 3,000 flight cycles 

after the effective date of this AD, whichever 

occurs later, do a high frequency eddy 

current (HFEC) or low frequency eddy 

current (LFEC) inspection for cracks on the 

area around certain fasteners of the access 

opening doubler on the left and right wing 

center spar lower cap, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin DC8–57A103, dated May 5, 

2010. If no crack is found, repeat the 

inspection thereafter at the applicable 

interval specified in paragraph 1.E., 

‘‘Compliance’’ of Boeing Alert Service 

Bulletin DC8–57A103, dated May 5, 2010. 

Repair 

(h) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, do paragraphs (h)(1), (h)(2), and (h)(3) of 

this AD. 

(1) Before further flight, repair the crack in 

accordance with Boeing Alert Service 

Bulletin DC8–57A103, dated May 5, 2010. 

(2) Within 6,000 flight cycles after doing 

the most recent HFEC inspection, or within 

1,750 flight cycles after doing the most recent 

LFEC inspection; as applicable; do the 

inspection specified in paragraph (g) of this 

AD of the non-repaired area, and repeat the 

inspection of the non-repaired area thereafter 

at the applicable time in paragraph 1.E. 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin DC8–57A103, dated May 5, 2010. 

(3) Within the applicable times specified in 

paragraph 1.E. ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin DC8–57A103, dated May 5, 

2010, do the inspections of the repaired area, 

using the inspection defined in Method 101 

of Section 57–10–06, or Method 101 or 104 

of Section 57–10–16, of the McDonnell 

Douglas DC–8 Supplemental Inspection 

Document (SID), Report L26–011, Volume II, 

Revision 8, dated January 2005, as 

applicable. Repeat the inspection thereafter 

at the applicable intervals specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin DC8–57A103, dated May 5, 

2010. If any crack is found, before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(i) The inspections required by paragraph 

(h)(3) of this AD constitute compliance with 

paragraph (j) of AD 2008–25–05, Amendment 

39–15763, for the repaired area. All 

requirements of AD 2008–25–05 that are not 

specifically referenced in this paragraph 

remain fully applicable and require 

compliance. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Los Angeles 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) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

Related Information 

(k) For more information about this AD, 

contact Dara Albouyeh, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; telephone 

(562) 627–5222; fax (562) 627–5210; e-mail: 

dara.albouyeh@faa.gov. 

Issued in Renton, Washington, on March 7, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–5898 Filed 3–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF STATE 

22 CFR Parts 123 and 126 

[Public Notice 7258] 

RIN 1400–AC70 

Amendment to the International Traffic 

in Arms Regulations: Replacement 

Parts/Components and Incorporated 

Articles 

AGENCY: Department of State. 

ACTION: Proposed rule. 

SUMMARY: The Department of State is 

amending the International Traffic in 

Arms Regulations (ITAR) to update 

policies regarding replacement parts/ 

components and incorporated articles. 

DATES: The Department of State will 

accept comments on this proposed rule 

until April 14, 2011. 

ADDRESSES: Interested parties may 

submit comments within 30 days of the 

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