Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41659 

TABLE 1—COMPLIANCE TIMES

MSN— Initial compliance time— 

0012 ............ Before the accumulation of 16,200 total flight cycles, or 38,900 total flight hours, whichever occurs first. 

0017 ............ Before the accumulation of 16,200 total flight cycles, or within 38,000 total flight hours, whichever occurs first. 

(h) If no crack is found during the 

inspection required by paragraph (g) of this 

AD, repeat the inspection in paragraph (g) of 

this AD thereafter at intervals not to exceed 

7,400 flight cycles or 22,300 flight hours, 

whichever occurs first. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; 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 FAAapproved 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 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0173, 

dated August 17, 2010; and Airbus 

Mandatory Service Bulletin A330–53–3185, 

dated May 20, 2010; for related information. 

Material Incorporated by Reference 

(k) You must use Airbus Mandatory 

Service Bulletin A330–53–3185, excluding 

Appendix 01 and including Appendix 02, all 

dated May 20, 2010, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(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 Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; e-mail 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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 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 July 1, 

2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17403 Filed 7–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1158; Directorate 

Identifier 2010–NM–125–AD; Amendment 

39–16750; AD 2011–15–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

That AD currently requires repetitive 

inspections to detect damage of the 

sleeving and wire bundles of the boost 

pumps of the numbers 1 and 4 main fuel 

tanks, and of the auxiliary tank jettison 

pumps (if installed); replacement of any 

damaged sleeving with new sleeving; 

and repair or replacement of any 

damaged wires with new wires. For 

airplanes on which any burned wires 

are found, that AD also requires an 

inspection to detect damage of the 

conduit, and replacement of any 

damaged conduit with a serviceable 

conduit. This new AD reduces the 

initial compliance time and repetitive 

inspection interval in the existing AD. 

This AD was prompted by fleet 

information indicating that the 

repetitive inspection interval in the 

existing AD is too long because 

excessive chafing of the sleeving 

continues to occur much earlier than 

expected between scheduled 

inspections. We are issuing this AD to 

detect and correct abrasion of the Teflon 

sleeving and wires in the bundles of the 

fuel boost pumps for the numbers 1 and 

4 main fuel tanks and of the auxiliary 

tank jettison pumps (if installed), which 

could result in electrical arcing between 

the wires and aluminum conduit and 

consequent fire or explosion of the fuel 

tank. 

DATES: This AD is effective August 19, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 19, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1, fax 206–766–5680; e-mail 

me.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 

98057–3356. 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 

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41660 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6505; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede an airworthiness 

directive (AD) 97–26–07, Amendment 

39–10250 (62 FR 65352, December 12, 

1997). That AD applies to the specified 

products. The NPRM published in the 

Federal Register on December 14, 2010 

(75 FR 77793). That NPRM proposed to 

continue to require repetitive 

inspections to detect damage of the 

sleeving and wire bundles of the boost 

pumps of the numbers 1 and 4 main fuel 

tanks, and of the auxiliary tank jettison 

pumps (if installed); replacement of any 

damaged sleeving with new sleeving; 

and repair or replacement of any 

damaged wires with new wires. For 

airplanes on which any burned wires 

are found, that NPRM also proposed to 

continue to require an inspection to 

detect damage of the conduit, and 

replacement of any damaged conduit 

with a serviceable conduit. That NPRM 

proposed to reduce the initial 

compliance time and repetitive 

inspection interval in the existing AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Change Heading for 

Restated Requirements 

United Airlines (UA) asked that we 

change the heading titled ‘‘Restatement 

of Requirements of AD 96–26–06, 

Amendment 39–9870,’’ which precedes 

paragraph (g) of the NPRM, to 

‘‘Restatement of Requirements of AD 

97–26–07, Amendment 39–10250. UA 

pointed out that AD 97–26–07 

superseded AD 96–26–06. 

We agree with UA for the reason 

provided. Although certain 

requirements in AD 96–26–06 are 

carried over in AD 97–26–07—and in 

this AD—those requirements are 

identified by the AD number within the 

applicable paragraphs. We have 

changed the heading preceding 

paragraph (g) of this AD accordingly. 

Request To Add Approved Alternate 

Method of Compliance 

UA asked that Boeing Alert Service 

Bulletin 747–28A2204, Revision 2, 

dated September 1, 2005, be included in 

paragraphs (g), (i), (j), and (k) of the 

NPRM. UA stated that Boeing Alert 

Service Bulletin 747–28A2204, Revision 

2, dated September 1, 2005, was 

approved as an alternative method of 

compliance (AMOC) to the requirements 

of paragraph (a) of AD 97–26–07. 

We partially agree with UA. We agree 

that Revision 2, dated September 1, 

2005, of Boeing Alert Service Bulletin 

747–28A2204, was reviewed by the 

FAA, and approved as an AMOC to the 

requirements of paragraph (a) of AD 97– 

26–07. We do not agree that Boeing 

Alert Service Bulletin 747–28A2204, 

Revision 2, dated September 1, 2005, 

should be added to the requested 

paragraphs because those paragraphs are 

part of the restatement of the 

requirements of AD 97–26–07. However, 

we have added a new paragraph (p) to 

this AD (and reidentified subsequent 

paragraphs) to give operators credit for 

using Boeing Alert Service Bulletin 

747–28A2204, Revision 2, dated 

September 1, 2005, to accomplish the 

specified actions. 

Request To Include Terminating Action 

UA asked that terminating action be 

included in the NPRM. UA stated that 

it believes Boeing is developing a 

solution that would terminate the 

inspections required by the NPRM. 

We acknowledge the comment from 

UA. However, Boeing has not submitted 

a revised service bulletin with 

terminating action for the repetitive 

inspections. We are aware that Boeing is 

developing a solution to the wire 

chafing issue, but until a modification is 

approved and available we are unable to 

reference it in the AD. However, under 

the provisions of paragraph (q) of this 

AD, we will consider requests for 

accomplishing a terminating 

modification if data are submitted to 

substantiate that it would provide an 

acceptable level of safety. We have 

made no change to the AD in this 

regard. 

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 changes described previously. 

We have determined that these changes 

will neither increase the economic 

burden on any operator nor increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 215 

airplanes of U.S. registry. The new 

requirements of this AD add no 

additional economic burden. The 

current costs for this AD are repeated 

below for the convenience of affected 

operators. 

The actions that are required by AD 

97–26–07 and retained in this AD take 

about 4 work-hours per airplane, at an 

average labor rate of $85 per work-hour. 

Based on these figures, the estimated 

cost of the currently required actions is 

$73,100, or $340 per airplane, 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, 

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 

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. 

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Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41661 

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) 

97–26–07, Amendment 39–10250 (62 

FR 65352, December 12, 1997), and 

adding the following new AD: 

2011–15–03 The Boeing Company: 

Amendment 39–16750; Docket No. 

FAA–2010–1158; Directorate Identifier 

2010–NM–125–AD. 

Effective Date 

(a) This AD is effective August 19, 2011. 

Affected ADs 

(b) This AD supersedes AD 97–26–07, 

Amendment 39–10250. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 747–100, –100B, –100B 

SUD, –200B, –200C, –200F, –300, –400, 

–400D, –400F, 747SR, and 747SP series 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD was prompted by fleet 

information indicating that the repetitive 

inspection interval in the existing AD is too 

long because excessive chafing of the 

sleeving continues to occur much earlier than 

expected between scheduled inspections. 

The Federal Aviation Administration is 

issuing this AD to detect and correct abrasion 

of the Teflon sleeving and wires in the 

bundles of the fuel boost pumps for the 

numbers 1 and 4 main fuel tanks and of the 

auxiliary tank jettison pumps (if installed), 

which could result in electrical arcing 

between the wires and aluminum conduit 

and consequent fire or explosion of the fuel 

tank. 

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 97–26– 

07, Amendment 39–10250 

Inspections/Repair or Replace if Necessary 

(g) Perform an initial inspection to detect 

damage of the sleeving and wire bundles of 

the forward and aft boost pumps of the 

numbers 1 and 4 main fuel tanks, and of the 

wire bundles of the auxiliary tank jettison 

pumps (if installed), in accordance with 

Boeing Alert Service Bulletin 747–28A2204, 

dated December 19, 1996; Boeing Service 

Bulletin 747–28A2204, Revision 1, dated 

October 30, 1997; or Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010; at the time specified in 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable. After the effective date of this AD, 

only Revision 3 of Boeing Alert Service 

Bulletin 747–28A2204 may be used. 

(1) For airplanes having line numbers 001 

through 432 inclusive: Inspect within 120 

days after January 21, 1997 (the effective date 

of AD 96–26–06, amendment 39–9870, which 

was superseded by AD 97–26–07). 

(2) For airplanes having line numbers 433 

and subsequent: Inspect at the later of the 

times specified in paragraphs (g)(2)(i) or 

(g)(2)(ii) of this AD. 

(i) Prior to the accumulation of 20,000 

flight cycles or 60,000 flight hours, 

whichever occurs first; or 

(ii) Within 120 days after December 29, 

1997 (the effective date of AD 97–26–07). 

(h) Repeat the inspection required by 

paragraph (g) of this AD at intervals not to 

exceed 20,000 flight cycles or 60,000 flight 

hours since the last inspection, whichever 

occurs first, until the first inspection required 

by paragraph (n) of this AD has been 

accomplished. 

(i) If any damaged sleeving is found, prior 

to further flight, replace the sleeving with 

new sleeving, in accordance with Boeing 

Alert Service Bulletin 747–28A2204, dated 

December 19, 1996; Boeing Service Bulletin 

747–28A2204, Revision 1, dated October 30, 

1997; or Boeing Alert Service Bulletin 747– 

28A2204, Revision 3, dated March 11, 2010. 

After the effective date of this AD, only 

Revision 3 of Boeing Alert Service Bulletin 

747–28A2204 may be used. 

(j) If any damaged wire is found, prior to 

further flight, repair or replace the wire with 

a new wire, in accordance with Boeing Alert 

Service Bulletin 747–28A2204, dated 

December 19, 1996, Boeing Service Bulletin 

747–28A2204, Revision 1, dated October 30, 

1997; or Boeing Alert Service Bulletin 747– 

28A2204, Revision 3, dated March 11, 2010. 

After the effective date of this AD, only 

Revision 3 of Boeing Alert Service Bulletin 

747–28A2204 may be used. 

(k) If any burned wire is found, prior to 

further flight, perform an inspection to detect 

damage of the conduit, in accordance with 

Boeing Alert Service Bulletin 747–28A2204, 

dated December 19, 1996; Boeing Service 

Bulletin 747–28A2204, Revision 1, dated 

October 30, 1997; or Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010. If any damage is found, prior 

to further flight, replace the conduit with a 

serviceable conduit, in accordance with 

Boeing Alert Service Bulletin 747–28A2204, 

dated December 19, 1996; Boeing Service 

Bulletin 747–28A2204, Revision 1, dated 

October 30, 1997; or Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010. After the effective date of 

this AD, only Revision 3 of Boeing Alert 

Service Bulletin 747–28A2204 may be used. 

(l) For airplanes having line numbers 433 

and subsequent: Within 14 days after 

accomplishing the initial inspection required 

by paragraph (g) of this AD, submit a report 

of any damaged sleeving (i.e., holes, breaks, 

cuts, splits), damaged wire (i.e., worn or 

cracked insulation, exposed conductor, 

indication of arcing/burning), or damaged 

conduit to the Manager, Seattle Aircraft 

Certification Office (ACO), FAA, Transport 

Airplane Directorate, 1601 Lind Avenue, 

SW., Renton, WA 98057–3356; fax (425) 227– 

1181. The report shall include the 

information specified in paragraphs (l)(1), 

(l)(2), (l)(3), (l)(4), and (l)(5) of this AD. 

Information collection requirements 

contained in this regulation have been 

approved by the Office of Management and 

Budget (OMB) under the provisions of the 

Paperwork Reduction Act of 1980 (44 U.S.C. 

3501 et seq.) and have been assigned OMB 

Control Number 2120–0056. 

(1) The airplane serial number. 

(2) The total hours’ time-in-service 

accumulated on the airplane. 

(3) The total number of flight cycles 

accumulated on the airplane. 

(4) A description of any damage found. 

(5) The location of where the damaged part 

was installed. 

(m) For airplanes having line numbers 433 

and subsequent: Within 14 days after 

accomplishing the initial inspection required 

by paragraph (g) of this AD, submit any 

damaged part to the Manager, Seattle ACO. 

The damaged part shall be tagged to include 

the information specified in paragraphs (l)(1), 

(l)(2), (l)(3), (l)(4), and (l)(5) of this AD. 

Additionally, operators shall align the inner 

sleeving, outer sleeving, and wire as installed 

in the airplane, and secure the sleeving and 

wiring in place by taping or other means 

when submitting the damaged part to the 

Manager, Seattle ACO. Information collection 

requirements contained in this regulation 

have been approved by the OMB under the 

provisions of the Paperwork Reduction Act of 

1980 (44 U.S.C. 3501 et seq.) and have been 

assigned OMB Control Number 2120–0056. 

New Reduced Inspection Intervals 

Repetitive Inspections 

(n) Do the next inspection required by 

paragraph (h) of this AD at the time specified 

in paragraph (n)(1) or (n)(2) of this AD, as 

applicable, in accordance with Boeing Alert 

Service Bulletin 747–28A2204, Revision 3, 

dated March 11, 2010. Repeat the inspection 

thereafter at intervals not to exceed 15,000 

flight hours. Accomplishing the initial 

inspection in this paragraph ends the 

repetitive inspection requirements of 

paragraph (h) of this AD. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done as of the effective date of this AD: Do 

the inspection at the earlier of the times 

specified in paragraph (n)(1)(i) and (n)(1)(ii) 

of this AD. 

(i) Within 15,000 flight hours after the most 

recent inspection, or within 6,000 flight 

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41662 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 

hours after the effective date of this AD, 

whichever occurs later. 

(ii) Within 20,000 flight cycles or 60,000 

flight hours after the most recent inspection 

required by paragraph (g) or (h) of this AD, 

whichever occurs first. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has not 

been done as of the effective date of this AD: 

Do the inspection before the accumulation of 

15,000 total flight hours, or within 6,000 

flight hours after the effective date of this AD, 

whichever occurs later. 

Paperwork Reduction Act Burden Statement 

(o) 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. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(p) Actions done before the effective date 

of this AD in accordance with Boeing Alert 

Service Bulletin 747–28A2204, Revision 2, 

dated September 1, 2005, are acceptable for 

compliance with the corresponding 

requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(1) The Manager, Seattle 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 ATTN: 

Tung Tran, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6505; fax (425) 917–6590. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(3) AMOCs approved previously in 

accordance with AD 97–26–07, Amendment 

39–10250, are approved as alternative 

methods of compliance with the 

corresponding requirements of this AD. 

Compliance time extensions approved 

previously in accordance with AD 97–26–07, 

are not approved as alternative methods of 

compliance for the compliance times 

required by paragraph (n) of this AD. 

Material Incorporated by Reference 

(r) You must use Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010, to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 747–28A2204, 

Revision 3, dated March 11, 2010, under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.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 July 1, 

2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17404 Filed 7–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0695; Directorate 

Identifier 2011–SW–001–AD; Amendment 

39–16740; AD 2011–14–05] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters, Inc. Model MD900 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD) 

for MD Helicopters, Inc. (MDHI) Model 

MD900 helicopters. That AD currently 

requires visually inspecting the main 

rotor lower hub assembly (lower hub) 

for a crack, and if you find a crack, 

before further flight, replacing the 

unairworthy lower hub with an 

airworthy lower hub. Additionally, 

within 10 days of finding a cracked 

lower hub, the existing AD requires 

reporting the finding to the Los Angeles 

Aircraft Certification Office (LAACO). 

That AD was prompted by two reports 

of cracks detected in the hub in the area 

near the flex beam bolt hole locations 

during maintenance on two MDHI 

Model MD900 helicopters. Since we 

issued that AD, we determined that one 

manufacturer had incorrectly inserted 

flanged bushings into the lower hub 

bore that resulted in local corrosion, 

leading to fatigue cracking. Examination 

of lower hubs from the other 

manufacturer shows correct bushing 

installation. Therefore, this amendment 

limits the applicability to the affected 

lower hubs; retains the visual inspection 

but at a different compliance time; adds 

an eddy current inspection; retains the 

requirement to replace a cracked lower 

hub with an airworthy lower hub before 

further flight; and removes the 

requirement to report to the LAACO. 

The actions specified by this AD are 

intended to detect a crack in the lower 

hub and prevent failure of the lower hub 

and subsequent loss of control of the 

helicopter. 

DATES: This AD is effective August 1, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 1, 2011. 

We must receive any comments on 

this AD by September 13, 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 AD, contact MD Helicopters Inc., 

Attn: Customer Support Division, 4555 

E. McDowell Rd., Mail Stop M615, 

Mesa, AZ 85215–9734, telephone 1– 

800–388–3378, fax 480–346–6813, or at 

http://www.mdhelicopters.com. 

mstockstill on DSK4VPTVN1PROD with RULES