58094 Federal Register / Vol. 76, No. 182 / Tuesday, September 20, 2011 / Rules and Regulations 

information technologies to provide 

increased opportunities for citizen 

access to Government information and 

services, and for other purposes. 

List of Subjects in 7 CFR Part 762 

Agriculture, Credit, Loan programs— 

Agriculture. 

For reasons discussed above, this rule 

amends 7 CFR part 762 as follows: 

PART 762—GUARANTEED FARM 

LOANS 

■ 1. Revise the authority citation for part 

762 to read as follows: 

Authority: 5 U.S.C. 301 and 7 U.S.C. 1989. 

■ 2. Amend § 762.130 by revising 

paragraphs (d)(4)(ii) and (d)(4)(iii)(C) to 

read as follows: 

§ 762.130 Loan approval and issuing the 

guarantee. 

* * * * * 

(d) * * * 

(4) * * * 

(ii) The guarantee fee is established by 

the Agency at the time the guarantee is 

obligated. The current fee schedule is 

available at http://www.fsa.usda.gov and 

any FSA office. Guaranteed fees may be 

adjusted annually based on factors that 

affect program costs. The nonrefundable 

fee is paid to the Agency by the lender. 

The fee may be passed on to the 

borrower and included in loan funds. 

The guarantee fee for the loan type will 

be calculated as follows: 

(A) FO guarantee fee = Loan Amount 

× % guaranteed × (FO percentage 

established by FSA). 

(B) OL guarantee fee = Loan Amount 

× % guaranteed × (OL percentage 

established by FSA). 

(C) CL guarantee fee = Loan Amount 

× % guaranteed × (CL percentage 

established by FSA). 

(iii) * * * 

(C) Loans to beginning or socially 

disadvantaged farmers involved in the 

direct Downpayment Loan Program or 

beginning farmers participating in a 

qualified State Beginning Farmer 

Program. 

* * * * * 

Signed on September 12, 2011. 

Bruce Nelson, 

Administrator, Farm Service Agency. 

[FR Doc. 2011–23724 Filed 9–19–11; 8:45 am] 

BILLING CODE 3410–05–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1163; Directorate 

Identifier 2009–NM–233–AD; Amendment 

39–16795; AD 2011–18–13] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Model 328– 

100 and –300 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

During a routine inspection, cracks have 

been found on an aeroplane at the lower 

wing panel rear trailing edge inboard of flap 

lever arm 1 (rib 5). A subsequent inspection 

of the other aeroplanes in that operator’s fleet 

revealed several more aeroplanes with cracks 

at the same location. This condition, if not 

corrected, could lead to structural failure of 

the affected wing panel, possibly resulting in 

the wing separating from the airplane with 

consequent loss of control. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 25, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 25, 2011. 

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 2, 2010 (75 FR 

75159), and proposed to supersede AD 

2008–10–51, Amendment 39–15535 (73 

FR 30752, May 29, 2008). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During a routine inspection, cracks have 

been found on an aeroplane at the lower 

wing panel rear trailing edge inboard of flap 

lever arm 1 (rib 5). A subsequent inspection 

of the other aeroplanes in that operator’s fleet 

revealed several more aeroplanes with cracks 

at the same location. This condition, if not 

corrected, could lead to structural failure of 

the affected wing panel, possibly resulting in 

the wing separating from the airplane with 

consequent loss of control. 

To correct this unsafe condition, EASA 

[European Aviation Safety Agency] issued 

Emergency AD 2008–0087–E [dated May 8, 

2008] to require detailed visual inspections 

(DVI) of both the left (LH) and right (RH) 

wing panel rear trailing edge around rib 3 

and rib 5 and a subsequent Eddy Current 

inspection (NDI) [non-destructive inspection] 

of the same area to detect cracks, follow-up 

repair actions when cracks are found, and the 

reporting of all findings. The TC [type 

certificate] holder has now developed a 

modification, consisting of the cold 

expansion of the former lower wing panel 

CAMLOC holes together with the installation 

of new attachment material that will prevent 

the onset of cracks in the affected wing panel. 

For the reasons described above, this 

[EASA] AD retains the inspection and repair 

requirements of AD 2008–0087–E, which is 

superseded, adds repetitive inspections and 

a requirement to modify both the LH and RH 

wing panel rear trailing edges from rib 3 to 

rib 9. Modification does not constitute 

terminating action for the new repetitive 

inspection requirements of this AD. 

The new inspections are eddy current 

inspections. The modification includes 

cold expansion of the former lower wing 

panel CAMLOC holes and installation of 

new attachment material. 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 

considered the comments received. 

MCAI Reference Updates 

EASA issued AD 2009–0194R1 on 

March 10, 2011, which was corrected on 

March 22, 2011. References have been 

updated in Note 1 and paragraph (p) of 

this AD to include this revision. 


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Federal Register / Vol. 76, No. 182 / Tuesday, September 20, 2011 / Rules and Regulations 58095 

Request to Remove Repetitive 

Inspection Interval From Paragraph (h) 

of This AD 

Garner CAD Technic Design 

Organization (GCT DO) Airworthiness 

Office requested that the 400-flightcycle repetitive inspection interval be 

removed from paragraph (h) of the 

NPRM (75 FR 75159, December 2, 2010). 

GCT DO Airworthiness Office stated 

that, based on fatigue data, this 

repetitive inspection is not required, 

and is not specified in revised EASA AD 

2009–0194R1, dated March 10, 2011, 

and corrected on March 22, 2011. 

We agree. Based on fatigue data, we 

have determined that the 400-flightcycle repetitive inspection interval 

should be removed from paragraph (h) 

of this AD. The repetitive inspection 

was removed from revised EASA AD 

2009–0194R1, dated March 10, 2011, 

and corrected on March 22, 2011. 

Paragraph (h) of this AD has been 

changed accordingly. References to the 

400-flight-cycle repetitive inspections 

also were removed from paragraphs (i) 

and (j) of this AD. 

To ensure that operators get credit for 

the most recent inspection done in 

accordance with Dornier Alert Service 

Bulletin ASB–328J–57–015 or ASB– 

328–57–037, both Revision 1, both 

dated May 8, 2008; or 328 Support 

Services Alert Service Bulletin ASB– 

328J–57–015 or ASB–328–57–037, both 

Revision 2, both dated May 20, 2008; we 

have clarified paragraph (g) of this AD. 

We have replaced the phrase, ‘‘in 

accordance with the requirements of 

paragraph (h) of this AD,’’ with the 

phrase, ‘‘in accordance with Dornier 

Alert Service Bulletin ASB–328J–57– 

015 or ASB–328–57–037, both Revision 

1, both dated May 8, 2008; or 328 

Support Services Alert Service Bulletin 

ASB–328J–57–015 or ASB–328–57–037, 

both Revision 2, both dated May 20, 

2008.’’ 

Request for Extended Inspection 

Interval in Paragraph (i) of This AD 

GCT DO Airworthiness Office 

requested that the initial compliance 

time and repetitive inspection interval 

defined in paragraph (i) of the NPRM 

(75 FR 75159, December 2, 2010) be 

extended from 800 flight cycles to 1,500 

flight cycles. GCT DO Airworthiness 

Office stated that this extension has 

been allowed based on fatigue data, and 

was specified in revised EASA AD 

2009–0194R1, dated March 10, 2011, 

and corrected on March 22, 2011. 

We agree to extend the initial 

compliance time and repetitive 

inspection intervals for the reasons 

given by the commenter. Paragraph (i) of 

this AD has been changed accordingly. 

Request To Extend Threshold for PostModification Inspections 

GCT DO Airworthiness Office 

requested that based on fatigue data, the 

threshold for the post-modification 

initial inspection be extended from 800 

flight cycles to 25,000 flight cycles for 

the Model 328–100 airplane, and from 

800 flight cycles to 20,000 flight cycles 

for Model 328–300 airplanes, and that 

the repetitive inspections be extended 

from 800 flight cycles to 1,500 flight 

cycles. 

We agree to extend the threshold for 

post-modification initial inspections as 

requested. Based on fatigue data, the 

referenced EASA AD has included these 

extensions; therefore, we have added 

paragraph (k) to the AD to include the 

new compliance times. 

Additional Change to NPRM 

The NPRM (75 FR 75159, December 2, 

2010) would have allowed issuance of a 

special flight permit if a crack was 

found that ‘‘exceeds’’ 12.5 mm (0.49 

inch). We have changed paragraph 

(o)(4)(ii) of this AD to change the 

wording from ‘‘exceeds’’ to ‘‘is less than 

or equal to.’’ 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 49 products of U.S. registry. 

The actions that are required by AD 

2008–10–51 and retained in this AD 

take about 2 work-hours per product, at 

an average labor rate of $85 per workhour. Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $170 per product. 

We estimate that it will take about 8 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$11,600 per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$601,720, or $12,280 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this 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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 


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58096 Federal Register / Vol. 76, No. 182 / Tuesday, September 20, 2011 / Rules and Regulations 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing Amendment 39–15535 (73 FR 

30752, May 29, 2008) and adding the 

following new AD: 

2011–18–13 328 Support Services GmbH 

(Type Certificate Previously Held by 

AvCraft Aerospace GmbH; Fairchild 

Dornier GmbH; Dornier Luftfahrt 

GmbH): Amendment 39–16795. Docket 

No. FAA–2010–1163; Directorate 

Identifier 2009–NM–233–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 25, 2011. 

Affected ADs 

(b) This AD supersedes AD 2008–10–51, 

Amendment 39–15535 (73 FR 30752, May 29, 

2008). 

Applicability 

(c) This AD applies to 328 Support 

Services GmbH (Type Certificate previously 

held by AvCraft Aerospace GmbH; Fairchild 

Dornier GmbH; Dornier Luftfahrt GmbH) 

Model 328–100 and –300 airplanes; all serial 

numbers; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During a routine inspection, cracks have 

been found on an aeroplane at the lower 

wing panel rear trailing edge inboard of flap 

lever arm 1 (rib 5). A subsequent inspection 

of the other aeroplanes in that operator’s fleet 

revealed several more aeroplanes with cracks 

at the same location. This condition, if not 

corrected, could lead to structural failure of 

the affected wing panel, possibly resulting in 

the wing separating from the airplane with 

consequent loss of control. 

* * * * * 

The new inspections are eddy current 

inspections. The modification includes cold 

expansion of the former lower wing panel 

CAMLOC holes and installation of new 

attachment material. 

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. 

Restatement of Requirements of AD 2008– 

10–51 (73 FR 30752, May 29, 2008), With 

Updated Service Information and Removal 

of Certain Repetitive Inspections 

Repetitive Detailed Visual Inspections for 

Cracks 

(g) Within 10 flight cycles, or 10 flight 

hours, or 7 days, whichever occurs first after 

June 3, 2008 (the effective date of AD 2008– 

10–51 (73 FR 30752, May 29, 2008)): 

Accomplish a detailed visual inspection of 

both the left-hand (LH) and right-hand (RH) 

lower wing panel inboard and outboard of 

flap lever arm 1 (rib 5) for cracks, in 

accordance with the Accomplishment 

Instructions of Dornier Alert Service Bulletin 

ASB–328J–57–015 or ASB–328–57–037, both 

Revision 1, both dated May 8, 2008, as 

applicable; or 328 Support Services Alert 

Service Bulletin ASB–328J–57–015 or ASB– 

328–57–037, both Revision 2, both dated May 

20, 2008, as applicable. After the effective 

date of this AD, use only 328 Support 

Services Alert Service Bulletin ASB–328J– 

57–015 or ASB–328–57–037, both Revision 2, 

both dated May 20, 2008, as applicable. If no 

crack is detected, repeat the detailed visual 

inspection thereafter at intervals not to 

exceed 50 flight hours. If any crack is 

detected, before further flight, do an eddy 

current inspection, in accordance with 

Dornier Alert Service Bulletin ASB–328J–57– 

015 or ASB–328–57–037, both Revision 1, 

both dated May 8, 2008, as applicable; or 328 

Support Services Alert Service Bulletin ASB– 

328J–57–015 or ASB–328–57–037, both 

Revision 2, both dated May 20, 2008, as 

applicable. 

Eddy Current Inspections for Cracks 

(h) Except as required by paragraph (g) of 

this AD, within 400 flight hours or 3 months 

after June 3, 2008, whichever occurs first: 

Accomplish an eddy current inspection for 

cracking of both the LH and RH lower wing 

panel in the vicinity of rib 3 and inboard and 

outboard of flap lever arm 1 (rib 5), in 

accordance with the Accomplishment 

Instructions of Dornier Alert Service Bulletin 

ASB–328J–57–015 or ASB–328–57–037, both 

Revision 1, both dated May 8, 2008, as 

applicable; or 328 Support Services Alert 

Service Bulletin ASB–328J–57–015 or ASB– 

328–57–037, both Revision 2, both dated May 

20, 2008, as applicable. After the effective 

date of this AD, use only 328 Support 

Services Alert Service Bulletin ASB–328J– 

57–015 or ASB–328–57–037, both Revision 2, 

both dated May 20, 2008, as applicable. 

Accomplishment of the eddy current 

inspection terminates the detailed visual 

inspection required by paragraph (g) of this 

AD. 

New Requirements of This AD 

New Repetitive Intervals for Eddy Current 

Inspections 

(i) Within 1,500 flight cycles after the most 

recent eddy current inspection done in 

accordance with the applicable service 

bulletin listed in table 1 of this AD, or within 

60 days after the effective date of this AD, 

whichever occurs later, do an eddy current 

inspection for cracking of the lower wing 

panel (outside) around the flap lever arm 1 

(rib 5), in accordance with the 

Accomplishment Instructions of 328 Support 

Services Alert Service Bulletin ASB–328–57– 

037 (for Model 328–100 airplanes) or ASB– 

328J–57–015 (for Model 328–300 airplanes), 

both Revision 2, both dated May 20, 2008. 

Repeat the inspection thereafter at intervals 

not to exceed 1,500 flight cycles, except as 

provided by paragraph (k) of this AD. 

TABLE 1—SERVICE BULLETINS

Service Bulletin Revision Date 

Dornier Alert Service Bulletin ASB–328–57–037 ............................................................................................ 1 May 8, 2008. 

Dornier Alert Service Bulletin ASB–328J–57–015 .......................................................................................... 1 May 8, 2008. 

328 Support Services Alert Service Bulletin ASB–328–57–037 ..................................................................... 2 May 20, 2008. 

328 Support Services Alert Service Bulletin ASB–328J–57–015 ................................................................... 2 May 20, 2008. 


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Federal Register / Vol. 76, No. 182 / Tuesday, September 20, 2011 / Rules and Regulations 58097 

Inspection and Modification of Lower Wing 

Panel 

(j) Within 24 months after the effective date 

of this AD, do an eddy current inspection for 

cracking of the lower wing panel (outside) 

around the flap lever arm 1 (rib 5). If no 

cracking is found, within 24 months after the 

effective date of this AD, modify the lower 

wing panel by doing a cold expansion of the 

CAMLOC holes and installing new 

attachment material from rib 9 LH to rib 9 

RH. Do all actions required by this paragraph 

in accordance with the Accomplishment 

Instructions of 328 Support Services Service 

Bulletin SB–328–57–481 (for Model 328–100 

airplanes) or SB–328J–57–230 (for Model 

328–300 airplanes), both Revision 1, both 

dated October 15, 2009. 

(k) After the modification required by 

paragraph (j) is done, do the eddy current 

inspection required by paragraph (i) of this 

AD at the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD. Repeat 

the inspections thereafter at the intervals 

specified in paragraph (i) of this AD. 

(1) For Model 328–100 airplanes: Within 

25,000 flight cycles after accomplishing the 

modification specified in paragraph (j) of this 

AD. 

(2) For Model 328–300 airplanes: Within 

20,000 flight cycles after accomplishing the 

modification specified in paragraph (j) of this 

AD. 

Repair 

(l) If any cracking is found during any 

inspection required by this AD, before further 

flight contact 328 Support Services GmbH for 

repair instructions and do the repair using a 

method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

Inspections Accomplished According to 

Previous Issues of Service Bulletins 

(m) Inspections accomplished before the 

effective date of this AD according to Dornier 

Alert Service Bulletin ASB–328–57–037 or 

Dornier Alert Service Bulletin ASB–328J–57– 

015, both Revision 1, both dated May 8, 2008, 

as applicable, are considered acceptable for 

compliance with the inspection requirements 

of paragraphs (i) and (j) of this AD. 

Report 

(n) At the applicable times specified in 

paragraphs (n)(1) and (n)(2) of this AD: Send 

328 Support Services GmbH a report of 

findings (both positive and negative) found 

during each inspection required by 

paragraphs (g), (h), (i), and (j) of this AD. The 

report must include the inspection results, a 

description of any cracks found, the airplane 

serial number, and the number of landings 

and flight hours on the airplane. Send the 

report to 328 Support Services GmbH, Global 

Support Center, P.O. Box 1252, D–82231 

Wessling, Federal Republic of Germany; 

Telephone +49 8153 88111 6666; fax +49 

8153 88111 6565; e-mail: 

gsc.op@328support.de. 

(1) For any inspection done on or after the 

effective date of this AD: Within 30 days after 

the inspection. 

(2) For any inspection done before the 

effective date of this AD: Within 30 days after 

the effective date of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

EASA Airworthiness Directive 2009– 

0194R1, dated March 10, 2011, corrected 

March 22, 2011, gives credit for eddy current 

inspections conducted in accordance with 

the maintenance review board tasks. We are 

not giving credit for those inspections. 

Other FAA AD Provisions 

(o) 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: 

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. Information may be e-mailed 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. 

(3) Reporting Requirements: 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. 

(4) Special Flight Permits: Special flight 

permits may be issued in accordance with 

sections 21.197 and 21.199 of the Federal 

Aviation Regulations (14 CFR 21.197 and 

21.199) to operate the airplane to a location 

where the requirements of paragraphs (g), (h), 

(i), (j), (k), and (l) of this AD can be done if 

the following conditions are met: 

(i) The initial inspection required by 

paragraph (g) of this AD must be 

accomplished. 

(ii) If a crack indication is less than or 

equal to 12.5 mm (0.49 inch), the Manager, 

International Branch, ANM–116, concurs 

with issuance of the special flight permits. 

Related Information 

(p) Refer to MCAI EASA Airworthiness 

Directive 2009–0194R1, dated March 10, 

2011, corrected March 22, 2011, and the 

service bulletins listed in table 2 of this AD, 

for related information. 

TABLE 2—RELATED SERVICE BULLETINS

Service Bulletin Revision Date 

328 Support Services Alert Service Bulletin ASB–328–57–037 ..................................................................... 2 May 20, 2008. 

328 Support Services Alert Service Bulletin ASB–328J–57–015 ................................................................... 2 May 20, 2008. 

328 Support Services Service Bulletin SB–328–57–481 ................................................................................ 1 October 15, 2009. 

328 Support Services GmbH Service Bulletin SB–328J–57–230 .................................................................. 1 October 15, 2009. 

Material Incorporated by Reference 

(q) You must use the service information 

contained in table 3 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 


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58098 Federal Register / Vol. 76, No. 182 / Tuesday, September 20, 2011 / Rules and Regulations 

TABLE 3—ALL MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

328 Support Services Alert Service Bulletin ASB–328–57–037 ..................................................................... 2 May 20, 2008. 

328 Support Services Alert Service Bulletin ASB–328J–57–015 ................................................................... 2 May 20, 2008. 

328 Support Services Service Bulletin SB–328–57–481 ................................................................................ 1 October 15, 2009. 

328 Support Services GmbH Service Bulletin SB–328J–57–230 .................................................................. 1 October 15, 2009. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact 328 Support Services GmbH, 

Global Support Center, P.O. Box 1252, D– 

82231 Wessling, Federal Republic of 

Germany; telephone +49 8153 88111 6666; 

fax +49 8153 88111 6565; e-mail 

gsc.op@328support.de; Internet http:// 

www.328support.de. 

(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 NARA, 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 August 

19, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22032 Filed 9–19–11; 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; Amendment 

39–16805; AD 2011–18–23] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 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, and DC– 

8–43 airplanes; Model DC–8–50 series 

airplanes; Model DC–8F–54 and DC– 

8F–55 airplanes; Model DC–8–60 series 

airplanes; Model DC–8–60F series 

airplanes; Model DC–8–70 series 

airplanes; and Model DC–8–70F series 

airplanes. This AD requires 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 AD was prompted by 

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 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. 

DATES: This AD is effective October 25, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 25, 2011. 

ADDRESSES: For service information 

identified in this 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 

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: Dara 

Albouyeh, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: (562) 627–5222; fax: (562) 627– 

5210; e-mail: dara.albouyeh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

March 15, 2011 (76 FR 13926). That 

NPRM proposed to 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response to each comment. 

Request To Revise Paragraph (h)(3) of 

the NPRM 

Boeing requested that we revise 

paragraph (h)(3) of the NPRM (76 FR 

13926, March 15, 2011) to refer to 

‘‘Method 101 and 104,’’ instead of 

‘‘Method 101 or 104.’’ Boeing explained 

that Methods 101 and 104 should be 

used when using Section 57–10–16 of 

the McDonnell Douglas DC–8 

Supplemental Inspection Document 

(SID) Report L26–011, Volume II, 

Revision 8, dated January 2005. Boeing 

stated that ‘‘Method 101 and 104’’ is 

correctly referenced in the service 

information. 

We agree. We have clarified the 

reference as ‘‘Methods 101 and 104’’ in 

paragraph (h)(3) of the final rule for the 

reasons stated by Boeing. 


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