Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations 21237 

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), and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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: 

2008–08–26 Boeing: Amendment 39–15480. 

Docket No. FAA–2007–29063; 

Directorate Identifier 2007–NM–049–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective May 27, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 767–

200, –300, –300F, and –400ER series 

airplanes, certificated in any category; as 

identified in Boeing Special Attention 

Service Bulletin 767–30–0047, dated January 

25, 2007; and Boeing Special Attention 

Service Bulletin 767–30–0048, dated January 

25, 2007. 

Unsafe Condition 

(d) This AD results from a report of charred 

insulation blankets and burned wires around 

the forward gray water composite drain mast 

found during an inspection of the forward 

cargo compartment. We are issuing this AD 

to prevent a fire near a composite drain mast 

and possible disruption of the electrical 

power system caused by a lightning strike on 

a composite drain mast, which could result 

in the loss of several functions essential for 

safe flight. 

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. 

Inspection To Determine Material of Gray 

Water Drain Mast 

(f) Within 60 months after the effective 

date of this AD, inspect the forward and aft 

gray water drain masts to determine whether 

the drain mast is made of aluminum or 

composite. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the material of the forward and 

aft gray water drain masts can be 

conclusively determined from that review. 

(1) For any aluminum gray water drain 

mast identified during the inspection or 

records check required by paragraph (f) of 

this AD, no further action is required by this 

AD for that drain mast only. 

(2) For any composite gray water drain 

mast identified during the inspection or 

records check required by paragraph (f) of 

this AD, do the actions specified in 

paragraph (g) of this AD. 

Installation of New Ground Bracket and 

Bonding Jumper 

(g) For any composite gray water drain 

mast identified during the inspection or 

records check required by paragraph (f) of 

this AD: Within 60 months after the effective 

date of this AD, install a bonding jumper 

between the new ground bracket and the 

clamp on the tube of the gray water 

composite drain mast, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 767–30–

0047, dated January 25, 2007 (for Model 767–

200, –300, and –300F series airplanes); and 

Boeing Special Attention Service Bulletin 

767–30–0048, dated January 25, 2007 (for 

Model 767–400ER series airplanes). 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install, on any airplane, a 

composite gray water drain mast, unless a 

new ground bracket and bonding jumper are 

also installed, as specified in paragraph (g) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office, 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. 

Material Incorporated by Reference 

(j) You must use Boeing Special Attention 

Service Bulletin 767–30–0047, dated January 

25, 2007; or Boeing Special Attention Service 

Bulletin 767–30–0048, dated January 25, 

2007; as applicable; 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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference 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/

code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on April 7, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–8317 Filed 4–18–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–29029; Directorate 

Identifier 2007–NM–175–AD; Amendment 

39–15477; AD 2008–08–23] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–200C Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Boeing Model 737–200C series 

airplanes. This AD requires revising the 

FAA-approved maintenance inspection 

program to include inspections that will 

give no less than the required damage 

tolerance rating for each structural 

significant item (SSI), doing repetitive 

inspections to detect cracks of all SSIs, 

and repairing cracked structure. This 

AD results from a report of incidents 

involving fatigue cracking in transport 

category airplanes that are approaching 

or have exceeded their design service 

objective. We are issuing this AD to 

maintain the continued structural 

integrity of the entire fleet of Model 

737–200C series airplanes. 

DATES: This AD is effective May 27, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 


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21238 Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations 

of a certain publication listed in this AD 

as of May 27, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

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 (telephone 800–647–5527) 

is the 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590. 

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 all 

Boeing Model 737–200C series 

airplanes. That NPRM was published in 

the Federal Register on August 23, 2007 

(72 FR 48243). That NPRM proposed to 

require revising the FAA-approved 

maintenance inspection program to 

include inspections that will give no 

less than the required damage tolerance 

rating for each structural significant 

item (SSI), doing repetitive inspections 

to detect cracks of all SSIs, and 

repairing cracked structure. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the one commenter. 

Request To Allow Alternative 

Inspections for Previously Repaired/ 

Altered Structure 

Boeing requests that the NPRM be 

revised to include a provision for 

alternative inspections when a repair 

area prohibits operators from doing the 

inspections specified in paragraph (h) of 

the NPRM. Boeing requests that the 

initial alternative inspection be done 

within 12 months after the repair is 

discovered during the initial inspection 

required by paragraph (h). Boeing points 

out that a similar provision was 

provided in paragraph (e) of AD 98–11–

04 R1, amendment 39–10984 (64 FR 

987, January 7, 1999). Boeing states that 

including such a provision will assist 

operators. 

We agree. We have added a new 

paragraph (i) to this AD (and 

reidentified subsequent paragraphs) that 

provides alternative inspections to those 

in paragraph (h) of this AD. 

Request To Clarify Certain Sections of 

the Preamble of the NPRM 

Boeing requests that certain sections 

in the preamble of the NPRM be 

clarified for the following reasons: 

1. Boeing states that Advisory Circular 

(AC) No. 91–56, ‘‘Supplemental 

Structural Inspection Program for Large 

Transport Category Airplanes,’’ dated 

May 6, 2001, applies to airplanes 

certified under the fail-safe and fatigue 

requirements of Civil Air Regulations 

(CAR) 4b or part 25 of the Federal 

Aviation Regulations (14 CFR part 25), 

not damage tolerance structural 

requirements as stated in the ‘‘Issuance 

of Advisory Circular (AC)’’ section. 

2. Boeing notes that the ‘‘Other 

Relevant Rulemaking’’ section identifies 

the strut as one of the affected SSIs for 

Model 737–100, –200, and –200C series 

airplanes. Boeing states that those 

airplanes do not have an engine strut. 

3. Boeing states that Boeing Document 

D6–37089, ‘‘Supplemental Structural 

Inspection Document for Model 737–

100/200/200C Airplanes,’’ Revision E, 

dated May 2007 (referred to in the 

NPRM as the appropriate source of 

service information for the required 

actions), does not describe procedures 

for repairing cracked structure, as 

specified in the ‘‘Relevant Service 

Information’’ section. 

We agree with Boeing that the 

identified sections could be clarified. 

For the first two items we agree with 

Boeing’s statements. On the third item, 

while the document does not specify 

individual repair procedures for each 

specific SSI, it does specify that all 

repairs must be approved. However, no 

change has been made to the final rule 

since the identified sections of the 

NPRM do not reappear in the final rule. 

Explanation of Change to Reported 

Incidents 

We have revised the AD to specify 

that this AD results from a report of 

incidents involving fatigue cracking 

only. 

Explanation of Change to Costs of 

Compliance 

The requirements for the baseline 

structure of Model 737–200C series 

airplanes are currently described in 14 

CFR 121.1109(c)(1) and 129.109(b)(1), 

not in 14 CFR 121.370(a) and 129.16 as 

indicated in the third paragraph of the 

Cost of Compliance section of the 

NPRM. Therefore, we have revised the 

Costs of Compliance section of the AD 

accordingly. 

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 also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

There are about 49 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Cost 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Revision of maintenance 

inspection program.

1,000, per operator (3 

U.S. operators).

$80 $80,000 per operator ...... 9 $240,000. 

Inspections ....................... 500 per airplane ............. 80 $40,000, per airplane, 

per inspection cycle.

9 $360,000, per inspection 

cycle. 


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Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations 21239 

The number of work hours, as 

indicated above, is presented as if the 

accomplishment of the actions in this 

AD is to be conducted as ‘‘stand alone’’

actions. However, in actual practice, 

these actions for the most part will be 

done coincidentally or in combination 

with normally scheduled airplane 

inspections and other maintenance 

program tasks. Therefore, the actual 

number of necessary additional work 

hours will be minimal in many 

instances. Additionally, any costs 

associated with special airplane 

scheduling will be minimal. 

Further, compliance with this AD will 

be a means of compliance with the aging 

airplane safety final rule (AASFR) for 

the baseline structure of Model 737–

200C series airplanes. The AASFR final 

rule requires certain operators to 

incorporate damage tolerance 

inspections into their maintenance 

inspection programs. These 

requirements are described in 14 CFR 

121.1109(c)(1) and 129.109(b)(1). 

Accomplishment of the actions required 

by this AD will meet the requirements 

of these CFR sections for the baseline 

structure. The costs for accomplishing 

the inspection portion of this AD were 

accounted for in the regulatory 

evaluation of the AASFR final rule. 

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), and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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: 

2008–08–23 Boeing: Amendment 39–15477. 

Docket No. FAA–2007–29029; 

Directorate Identifier 2007–NM–175–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective May 27, 2008. 

Affected ADs 

(b) Accomplishing the actions required by 

paragraph (g) and the initial inspections 

required by paragraph (h) of this AD ends the 

requirements of AD 98–11–04 R1, 

amendment 39–10984, for Model 737–200C 

series airplanes only. Operators of Model 

737–100 and –200 series airplanes must 

continue to do the actions required by AD 

98–11–04 R1. 

Applicability 

(c) This AD applies to all Boeing Model 

737–200C series airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from a report of 

incidents involving fatigue cracking in 

transport category airplanes that are 

approaching or have exceeded their design 

service objective. We are issuing this AD to 

maintain the continued structural integrity of 

the entire fleet of Model 737–200C series 

airplanes. 

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. 

Service Information 

(f) The term ‘‘Revision E,’’ as used in this 

AD, means Boeing Document D6–37089, 

‘‘Supplemental Structural Inspection 

Document for Model 737–100/200/200C 

Airplanes,’’ Revision E, dated May 2007. 

Revision of the FAA-Approved Maintenance 

Inspection Program 

(g) At the applicable time specified in 

Table 1 of this AD, incorporate a revision 

into the FAA-approved maintenance 

inspection program that provides no less 

than the required damage tolerance rating 

(DTR) for each structural significant item 

(SSI) listed in Revision E. (The required DTR 

value for each SSI is listed in Revision E.) 

The revision to the maintenance inspection 

program must include and must be 

implemented in accordance with the 

procedures in Section 5.0, ‘‘Damage 

Tolerance Rating (DTR) System Application,’’

and Section 6.0, ‘‘SSI Discrepancy 

Reporting’’ of Revision E. Under the 

provisions of the Paperwork Reduction Act of 

1980 (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. 

TABLE 1.—COMPLIANCE TIME FOR REVISING MAINTENANCE INSPECTION PROGRAM

For airplanes with SSIs— Compliance time 

(1) Affected by the cargo configuration.Before the accumulation of 46,000 total flight cycles, or within 12 months after the effective date of this 

AD, whichever occurs later. 

(2) Not affected by the cargo configuration.Before the accumulation of 66,000 total flight cycles, or within 12 months after the effective date of this 

AD, whichever occurs later. 


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21240 Federal Register / Vol. 73, No. 77 / Monday, April 21, 2008 / Rules and Regulations 

Initial and Repetitive Inspections 

(h) Except as provided by paragraph (i) of 

this AD: At the applicable time specified in 

Table 2 of this AD, do the applicable initial 

inspections to detect cracks of all SSIs, in 

accordance with Revision E. Repeat the 

applicable inspections thereafter at the 

intervals specified in Section 3.0, 

‘‘Implementation’’ of Revision E. 

TABLE 2.—COMPLIANCE TIME FOR INITIAL INSPECTIONS

For airplanes with SSIs— Compliance time 

(1) Affected by the cargo configuration.Before the accumulation of 46,000 total flight cycles, or within 4,000 flight cycles measured from 12 

months after the effective date of this AD, whichever occurs later. 

(2) Not affected by the cargo configuration.Before the accumulation of 66,000 total flight cycles, or within 4,000 flight cycles measured from 12 

months after the effective date of this AD, whichever occurs later. 

(i) For any SSI that has been repaired or 

altered before the effective date of this AD 

such that the repair or design change affects 

your ability to accomplish the actions 

required by paragraph (h) of this AD: You 

must request FAA approval of an alternative 

method of compliance (AMOC) in 

accordance with section 39.17 of the Federal 

Aviation Regulations (14 CFR 39.17), at the 

initial compliance time specified in 

paragraph (h) of the AD; or do the actions 

specified in paragraphs (i)(1) and (i)(2) of this 

AD, at the times specified in those 

paragraphs, as an approved means of 

compliance with the requirements of 

paragraph (h) of this AD. 

(1) At the initial compliance time specified 

in paragraph (h) of the AD, identify each 

repair or design change to that SSI. 

(2) Within 12 months after the 

identification of a repair or design change 

required by paragraph (i)(1) of this AD, assess 

the damage tolerance characteristics of each 

SSI affected by each repair or design change 

to determine the effectiveness of the 

applicable SSID inspection for that SSI and 

if not effective, incorporate a revision into 

the FAA-approved maintenance inspection 

program to include a damage-tolerance based 

alternative inspection program for each 

affected SSI. Thereafter, inspect the affected 

structure in accordance with the alternative 

inspection program. The inspection method 

and compliance times (i.e., threshold and 

repeat intervals) of the alternative inspection 

program must be approved in accordance 

with the procedures specified in paragraph 

(l) of this AD. 

Repair 

(j) If any cracked structure is found during 

any inspection required by paragraph (h) or 

(i) of this AD, before further flight, repair the 

cracked structure using a method approved 

in accordance with the procedures specified 

in paragraph (l) of this AD. 

Inspection Program for Transferred 

Airplanes 

(k) Before any airplane that is subject to 

this AD and that has exceeded the applicable 

compliance times specified in paragraph (h) 

of this AD can be added to an air carrier’s 

operations specifications, a program for the 

accomplishment of the inspections required 

by this AD must be established in accordance 

with paragraph (k)(1) or (k)(2) of this AD, as 

applicable. 

(1) For airplanes that have been inspected 

in accordance with this AD: The inspection 

of each SSI must be done by the new operator 

in accordance with the previous operator’s 

schedule and inspection method, or the new 

operator’s schedule and inspection method, 

at whichever time would result in the earlier 

accomplishment for that SSI inspection. The 

compliance time for accomplishment of this 

inspection must be measured from the last 

inspection accomplished by the previous 

operator. After each inspection has been 

done once, each subsequent inspection must 

be performed in accordance with the new 

operator’s schedule and inspection method. 

(2) For airplanes that have not been 

inspected in accordance with this AD: The 

inspection of each SSI required by this AD 

must be done either before adding the 

airplane to the air carrier’s operations 

specification, or in accordance with a 

schedule and an inspection method approved 

by the Manager, Seattle Aircraft Certification 

Office (ACO), FAA. After each inspection has 

been done once, each subsequent inspection 

must be done in accordance with the new 

operator’s schedule. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Seattle ACO 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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair approval must 

specifically refer to this AD. 

Material Incorporated by Reference 

(m) You must use Boeing Document D6–

37089, ‘‘Supplemental Structural Inspection 

Document for Model 737–100/200/200C 

Airplanes,’’ Revision E, dated May 2007, to 

do the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The document contains the following 

errors: 

(i) Pages 2.0.3 and 2.0.4, Revision D, of 

Section 2.0 and pages F–14.5, Revision D, 

and F–14.6, Revision Blank, of Section 8.2 

exist; but are not specified in the List of 

Effective Pages. 

(ii) Pages 7.0.43 through 7.0.46 inclusive of 

Section 7.0 and pages W.34.1 and W.34.2 of 

Section 11.1, as specified in the List of 

Effective Pages, do not exist. 

(iii) The List of Effective Pages specifies 

incorrect revision levels for certain pages; the 

revision levels specified on each page are 

correct. 

(iv) None of the pages are dated. The issue 

date for each revision is specified in the 

Revision Highlights section. 

(2) 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. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(4) You may review copies of the service 

information incorporated by reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 8, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–8320 Filed 4–18–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26726; Directorate 

Identifier 2006–NM–205–AD; Amendment 

39–15479; AD 2008–08–25] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–400F and –400 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 


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