28594 Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 

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://dms.dot.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 the 

NPRM, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) 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 adding 

the following new AD: 

2007–11–04 Reims Aviation S.A.: 

Amendment 39–15061; Docket No. 

FAA–2007–26973; Directorate Identifier 

2007–CE–002–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 26, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model F406 

airplanes, serial numbers F406–0001 through 

F406–0092, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

This AD is issued following reports, on 

several aircraft, of important corrosion found 

on the ailerons bearings. 

This condition, if left uncorrected, could 

result in the loss of the roll control on the 

airplane. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within the next 100 hours time-inservice or 3 months, whichever occurs first 

after the effective date of this AD, and 

thereafter repetitively during a period not to 

exceed 12 months, inspect the aileron 

brackets and bearings and perform the 

lubrication of the aileron bearings in 

accordance with Reims Aviation Industries 

Service Bulletin No. F406–59, dated October 

24, 2005. 

(2) If corrosion is found during any 

inspection required in paragraph (f)(1) of this 

AD, before further flight, replace the 

damaged parts in accordance with Reims 

Aviation Industries Service Bulletin No. 

F406–59, dated October 24, 2005. 

Note 1: We established the repetitive 

inspection times of this AD so that they may 

coincide with annual inspections. 

Note 2: We encourage you to put Reims 

temporary revision No. 6 into the 

maintenance program of the F406 airplane 

(chapter 5 of the maintenance manual). 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: We 

added repetitive inspection requirements in 

this AD to coincide with the maintenance 

requirement in the service bulletin. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Staff, 

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: Mike Kiesov, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329–

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

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

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to Direction ge ́ne ́rale de l’aviation 

civile AD No. F–2005–177, dated November 

9, 2005; and Reims Aviation Industries 

Service Bulletin No. F406–59, dated October 

24, 2005, for related information. 

Material Incorporated by Reference 

(i) You must use Reims Aviation Industries 

Service Bulletin No. F406–59, dated October 

24, 2005, 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 Reims Aviation Industries, 

Ae ́rodrome de Reims Prunay, 51360 Prunay, 

A l’attention du Support Client; telephone: 

+33 (0)3.26.48.46.53; fax: +33 

(0)3.26.49.18.57. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; or 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/ibr-locations.html. 

Issued in Kansas City, Missouri, on May 

11, 2007. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–9618 Filed 5–21–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28254; Directorate 

Identifier 2007–NM–054–AD; Amendment 

39–15065; AD 2007–11–08] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 727 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to all Boeing Model 727 

airplanes. The existing AD requires a 

boost pump dry bay inspection to detect 

leakage of fuel through an arced-through 

conduit, and corrective action as 

necessary. The existing AD also requires 

repetitive inspections of the in-tank fuel 

boost pump wiring to detect chafing of 

the wire insulation, evidence of 

electrical arcing, or arc-through of the 

conduit wall, and applicable corrective 

action; and installation of sleeving over 

the in-tank fuel boost pump wires as a 

method to protect the wiring from 

chafing. This new AD removes certain 

inspection requirements from the 


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Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 28595 

existing AD. This new AD adds new 

repetitive inspections for damage of the 

electrical wire and sleeve that run to the 

fuel boost pump through a conduit in 

the fuel tank, and arcing damage of the 

conduit and signs of fuel leakage into 

the conduit; applicable investigative 

and corrective actions; and a new 

repetitive engine fuel suction feed 

operational test. Initiation of the new 

inspections terminates the requirements 

of the existing AD. This AD results from 

reports of a fuel tank explosion on a 

Model 727–200F airplane on the 

ground; and of chafed wires and a 

damaged power cable sleeve of a fuel 

boost pump that were discovered during 

an inspection required by an existing 

AD on a Model 737–300 airplane. We 

are issuing this AD to detect and correct 

chafing of the fuel boost pump electrical 

wiring and leakage of fuel into the 

conduit, and to prevent electrical arcing 

between the wiring and the surrounding 

conduit, which could result in arcthrough of the conduit, and consequent 

fire or explosion of the fuel tank. 

DATES: This AD becomes effective June 

6, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 6, 2007. 

On June 28, 1999 (64 FR 33394, June 

23, 1999), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing Alert Service 

Bulletin 727–28A0126, dated May 24, 

1999. 

We must receive any comments on 

this AD by July 23, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

You may examine the contents of the 

AD docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Room PL–401, Washington, DC. 

This docket number is FAA–2007–

28254; the directorate identifier for this 

docket is 2007–NM–054-AD. 

FOR FURTHER INFORMATION CONTACT: 

Suzanne Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6438; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 15, 1999, we issued AD 99–

12–52, amendment 39–11199 (64 FR 

33394, June 23, 1999) (originally issued 

on May 24, 1999, as telegraphic AD 

T99–12–52). That AD applies to all 

Boeing Model 727 series airplanes. That 

AD requires a boost pump dry bay 

inspection to detect leakage of fuel 

through an arced-through conduit, and 

corrective action, as necessary. That AD 

also requires repetitive detailed 

inspections of the in-tank fuel boost 

pump wiring to detect chafing of the 

wire insulation, evidence of electrical 

arcing, or arc-through of the conduit 

wall on Model 727 series airplanes, and 

applicable corrective action; and 

installation of sleeving over the in-tank 

fuel boost pump wires as a method to 

protect the wiring from chafing. That 

AD resulted from reports of severe wear 

of in-tank fuel boost pump wiring, and 

arc-through of the surrounding conduit 

on two Model 727 series airplanes. The 

actions specified in that AD are 

intended to prevent fuel tank explosion 

resulting from arc-through of the fuel 

boost pump wiring conduits. 

Actions Since AD Was Issued 

Since we issued that AD, we received 

a report that a fuel tank explosion 

occurred on a Model 727–200F airplane 

on the ground. Investigation revealed 

evidence of arcing in the metal conduit 

that carries power wires from the front 

spar through the fuel tank to the dry bay 

of the #1 aft fuel boost pump. In a 

separate incident, we received a report 

from Boeing that chafed power wires 

and a damaged power cable sleeve of a 

fuel boost pump were discovered during 

an inspection required by AD 99–12–52 

on a Model 737–300 series airplane. 

That inspection was done at 21,000 

flight hours rather than the repetitive 

interval of 30,000 flight hours specified 

by that AD. The fuel boost pump 

installation on certain Model 737 

airplanes is almost identical to the 

installation on Model 727 airplanes. 

Other Relevant Rulemaking 

Operators should note that we are 

considering issuing a separate AD to 

address the identified unsafe condition 

as it relates to Model 737 airplanes. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 727–28A0132, dated 

February 22, 2007. The alert service 

bulletin describes procedures for doing 

new repetitive detailed inspections for 

damage of the electrical wire and sleeve 

that run to the fuel boost pump through 

a conduit in the fuel tank, and for arcing 

damage of, and signs of fuel leakage 

into, the conduit; doing a new engine 

fuel suction feed operational test; doing 

related investigative and corrective 

actions, as applicable; and sending 

inspection results and damaged parts to 

the manufacturer. Related investigative 

and corrective actions include replacing 

the wire sleeve with a new, smaller wire 

sleeve; replacing, with BMS 13–

60T09C03G018 wire, any wire that is 

damaged or has any part number other 

than BMS 13–60T09C03G018 or BMS 

13–60T12C03G018; doing leak testing of 

the conduit if signs of fuel are 

discovered on the wire or sleeve during 

any inspection; and repairing any 

damaged conduit or replacing it with a 

new conduit. 

AD 99–12–52 refers to Boeing Alert 

Service Bulletin 727–28A0126, dated 

May 24, 1999, as the appropriate source 

of service information for 

accomplishment of the detailed 

inspection and related investigative/ 

corrective actions; that requirement is 

new paragraph (i) in this AD. That 

service bulletin has since been revised. 

Revision 1, dated May 18, 2000, is 

essentially the same as the original and 

provides no new actions. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. For this reason, we are issuing 

this AD to supersede AD 99–12–52. This 

new AD retains certain requirements of 

the existing AD. This AD also requires 

accomplishing the actions specified in 

the alert service bulletin described 

previously, which, when initiated, 

terminates certain requirements. 

Explanation of Changes Made to 

Existing AD 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 


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28596 Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 

The FAA has changed all references 

to a ‘‘detailed visual inspection’’ in the 

existing AD to ‘‘detailed inspection’’ in 

this action. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–28254; Directorate Identifier 

2007–NM–054–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. We will post all 

comments we receive, without change, 

to http://dms.dot.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the 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. We prepared a 

regulatory evaluation of the estimated 

costs to comply with this AD and placed 

it in the AD docket. See the ADDRESSES

section for a location to examine the 

regulatory evaluation. 

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 part 39 of the Federal 

Aviation Regulations (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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–11199 (64 

FR 33394, June 23, 1999) and adding the 

following new airworthiness directive 

(AD): 

2007–11–08 Boeing: Docket No. FAA–2007–

28254; Directorate Identifier 2007–NM–

054–AD; Amendment 39–15065. 

Effective Date 

(a) This AD becomes effective June 6, 2007. 

Affected ADs 

(b) This AD supersedes AD 99–12–52. 

Applicability 

(c) This AD applies to all Boeing Model 

727, 727C, 727–100, 727 –100C, 727–200, 

and 727–200F series airplanes, certificated in 

any category. 

Unsafe Condition 

(d) This AD results from reports of a fuel 

tank explosion on a Model 727–200F 

airplane on the ground, and chafed wires and 

a damaged power cable sleeve of a fuel boost 

pump that were discovered during an 

inspection required by an existing AD on a 

Model 737–300 airplane, which has a fuel 

boost pump installation that is almost 

identical to the installation on Model 727 

airplanes. We are issuing this AD to detect 

and correct chafing of the fuel boost pump 

electrical wiring and leakage of fuel into the 

conduit, and to prevent electrical arcing 

between the wiring and the surrounding 

conduit, which could result in arc-through of 

the conduit, and consequent fire or explosion 

of the fuel tank. 

Compliance 

(e) 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 Certain Requirements of AD 

99–12–52 

(f) For airplanes with 50,000 or more total 

flight hours as of June 28, 1999 (the effective 

date of AD 99–12–52): Within 20 days after 

June 28, 1999, accomplish the requirements 

of paragraph (i) of this AD. 

(g) For airplanes with less than 50,000 total 

flight hours, but more than 30,000 total flight 

hours, as of June 28, 1999: Within 30 days 

after June 28, 1999, accomplish the 

requirements of paragraph (i) of this AD. 

(h) For airplanes with 30,000 total flight 

hours or less, as of June 28, 1999: Within 90 

days after June 28, 1999, accomplish the 

requirements of paragraph (i) of this AD. 

Detailed Inspection, Corrective Action, and 

Installation 

(i) Perform a detailed inspection of the intank fuel boost pump wire bundles, and 


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Federal Register / Vol. 72, No. 98 / Tuesday, May 22, 2007 / Rules and Regulations 28597 

applicable corrective actions; and, except as 

provided in paragraph (j) of this AD, install 

sleeving over the wire bundles; in accordance 

with Boeing Alert Service Bulletin 727–

28A0126, dated May 24, 1999; Boeing 

Service Bulletin 727–28A0126, Revision 1, 

dated May 18, 2000; or Boeing Alert Service 

Bulletin 727–28A0132, dated February 22, 

2007. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Installation: Possible Deferral 

(j) Installation of sleeving over the wire 

bundles, as required by paragraph (i) of this 

AD, may be deferred if, within 18 months or 

6,000 flight hours, whichever occurs first, 

after accomplishment of the inspection and 

applicable corrective actions required by 

paragraph (i), the following actions are 

accomplished: Perform a detailed inspection 

of the in-tank fuel boost pump wire bundles, 

and applicable corrective actions; and install 

sleeving over the wire bundles; in accordance 

with Boeing Alert Service Bulletin 727–

28A0126, dated May 24, 1999, or Boeing 

Service Bulletin 727–28A0126, Revision 1, 

dated May 18, 2000; or Boeing Alert Service 

Bulletin 727–28A0132, dated February 22, 

2007. 

Repetitive Inspections and Corrective 

Actions 

(k) Repeat the detailed inspection and 

applicable corrective actions required by 

paragraphs (i) and (j) of this AD at intervals 

not to exceed 30,000 flight hours, until the 

initial inspection, applicable corrective 

actions, and engine fuel suction feed 

operational test required by paragraph (l) of 

this AD have been done. 

New Requirements of This AD 

Inspection, Test, and Related Investigative 

and Corrective Actions 

(l) For all airplanes: Within 120 days after 

the effective date of this AD or 5,000 flight 

hours after the last inspection or corrective 

action done before the effective date of this 

AD as required by paragraph (i), (j), or (k), as 

applicable, of this AD, whichever occurs 

later, do a detailed inspection for damage of 

the sleeve and electrical wire of the fuel 

boost pump, and do an engine fuel suction 

feed operational test; and, before further 

flight, do related investigative and corrective 

actions, as applicable; by doing all applicable 

actions in and in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 727–28A0132, dated 

February 22, 2007. Repeat the detailed 

inspection and engine fuel suction feed 

operational test thereafter at intervals not to 

exceed 15,000 flight cycles. Accomplishment 

of the initial inspection, applicable corrective 

actions, and engine fuel suction feed 

operational test of this paragraph terminates 

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

of this AD. 

Inspection Report and Disposition of 

Damaged Parts 

(m) At the applicable time(s) specified in 

paragraph (m)(1) or (m)(2) of this AD: Submit 

a report of the findings (both positive and 

negative) of any inspection required by this 

AD and send any damaged parts to the 

manufacturer, as described in Boeing Alert 

Service Bulletin 727–28A0132, dated 

February 22, 2007. The report must include 

the information specified in Appendix A of 

the alert service bulletin. Under the 

provisions of the Paperwork Reduction Act 

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

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) For any inspection done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) For any inspection done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(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 on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(3) AMOCs approved previously in 

accordance with AD 99–12–52 are approved 

as AMOCs for the corresponding provisions 

of this AD. 

Material Incorporated by Reference 

(o) You must use applicable Boeing service 

bulletins specified in Table 1 of this AD to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. 

TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE

Boeing service information Revision level Date 

Alert Service Bulletin 727–28A0126 .................................................................... Original .................................................. May 24, 1999. 

Alert Service Bulletin 727–28A0132 .................................................................... Original .................................................. February 22, 2007. 

Service Bulletin 727–28A0126 ............................................................................. 1 ............................................................ May 18, 2000. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 727–28A0132, 

dated February 22, 2007; and Boeing Service 

Bulletin 727–28A0126, Revision 1, dated 

May 18, 2000; in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On June 28, 1999 (64 FR 33394, June 

23, 1999), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 727–28A0126, 

dated May 24, 1999. 

(3) Contact Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 98124–

2207, for a copy of this service information. 

You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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 May 1, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–9799 Filed 5–21–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28253; Directorate 

Identifier 2007–NM–031–AD; Amendment 

39–15064; AD 2007–11–07] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


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