47032 Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 

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, 

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 MCAI Canadian Airworthiness 

Directive CF–2007–32, dated December 17, 

2007, and the de Havilland temporary 

revisions listed in Table 1 of this AD. 

Material Incorporated by Reference 

(i) You must use the applicable service 

information specified in Table 3 of this AD 

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 Bombardier, Inc., 

Bombardier Regional Aircraft Division, 123 

Garratt Boulevard, Downsview, Ontario M3K 

1Y5, Canada. 

(3) 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. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

De Havilland 

temporary revision— Dated— To the—

AWL–110 ............................ August 31, 2007 ................. Dash 8 Series 100 Maintenance Program Manual, Product Support Manual 1–8–7, 

Part 2, ‘‘Airworthiness Limitations List’’. 

AWL 2–43 ........................... August 31, 2007 ................. Dash 8 Series 200 Maintenance Program Manual, Product Support Manual 1–82–7, 

Part 2, ‘‘Airworthiness Limitations List’’. 

AWL 3–109 ......................... August 31, 2007 ................. Dash 8 Series 300 Maintenance Program Manual, Product Support Manual 1–83–7, 

Part 2, ‘‘Airworthiness Limitations List’’. 

Issued in Renton, Washington, on July 31, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–18430 Filed 8–12–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0406; Directorate 

Identifier 2007–NM–196–AD; Amendment 

39–15640; AD 2008–17–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

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 routine visual inspection, a crack 

has been found in the wing MLG (main 

landing gear) rib 5 forward attachment lug on 

two A310 in-service aircraft. Laboratory 

examination of one of the cracked ribs 

confirmed that the crack is due to the 

presence of pitting corrosion in the forward 

lug holes. Also on both aircraft medium to 

heavy corrosion was found in the forward 

lugs on the opposite wing after removal of 

the bushes. This situation if not detected, 

could affect the structural integrity of the 

MLG attachment. * * * 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 17, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 17, 2008. 

The Director of the Federal Register 

previously approved the incorporation 

by reference of Airbus Service Bulletin 

A310–57A2088, excluding Appendix 

01, dated November 6, 2006, listed in 

this AD, as of February 6, 2007 (72 FR 

2612, January 22, 2007). 

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 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1622; 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 April 7, 2008 (73 FR 18722). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During routine visual inspection, a crack 

has been found in the wing MLG (main 

landing gear) rib 5 forward attachment lug on 

two A310 in-service aircraft. Laboratory 

examination of one of the cracked ribs 

confirmed that the crack is due to the 

presence of pitting corrosion in the forward 

lug holes. Also on both aircraft medium to 

heavy corrosion was found in the forward 

lugs on the opposite wing after removal of 

the bushes. This situation if not detected, 

could affect the structural integrity of the 

MLG attachment. As an interim measure, 

Airbus published Alert Service Bulletin 

(ASB) A310–57A2088 to introduce a 

repetitive detailed visual inspection (DVI) of 

the forward attachment lug of MLG Rib 5. 

EASA issued Emergency Airworthiness 

Directive (EAD) 2006–0335–E [which 

corresponds to FAA AD 2007–02–09] to 

require the accomplishment of this repetitive 

DVI. 

In order to ensure the detection of any 

crack at an early stage in the forward lug of 

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

Rib 5 aft bearing attachment, the Type 

Certificate holder has developed a new 

inspection by means of ultrasonic method. 

For the reasons described above, this new 

inspection program is rendered mandatory by 

this AD, which cancels and replaces the 

requirement of EAD 2006–0335–E. 

The corrective action includes 

repairing or replacing MLG Rib 5, as 


hsrobinson on PROD1PC76 with RULES
Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 47033 

applicable. 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. 

Clarification of Certain Requirements 

Airbus asks that we revise paragraph 

(g)(2) of the NPRM to clarify the intent 

of Airbus Service Bulletin A310–57–

2090, Revision 01, dated December 19, 

2007. Airbus states that paragraph (g)(2) 

of the NPRM refers to that service 

bulletin for replacement of the MLG Rib 

5. However, Airbus clarifies that the 

intent of Service Bulletin A310–57–

2090 is not to provide instructions for 

the MLG Rib 5 replacement, but to 

introduce new bushes with increased 

interference fit into the aft bearing 

forward lug of MLG Rib 5. Airbus asks 

that paragraph (g)(2) of the NPRM be 

changed as follows, for clarification: 

‘‘Replacement of the MLG Rib 5 bushes 

with high interference fit in accordance 

with the instructions defined in Airbus 

Service Bulletin A310–57–2090. * * *’’

We agree that paragraph (g)(2) of this 

AD should be further clarified to 

address the commenter’s suggestion; 

therefore, we have changed that 

paragraph accordingly. 

Airbus also asks that the last sentence 

of paragraphs (g)(3) and (g)(4)(ii) of the 

NPRM be changed to remove the 

reference to Airbus Service Bulletin 

A310–57–2090, Revision 01, dated 

December 19, 2007, when the MLG Rib 

5 replacement is in question. Airbus 

asks that paragraphs (g)(3) and (g)(4)(ii) 

of the NPRM be changed as follows, for 

clarification: ‘‘After MLG Rib 5 

replacement, whether Airbus Service 

Bulletin A310–57–2090, Revision 01, 

dated December 19, 2007 is not 

accomplished: * * *’’

We agree that paragraphs (g)(3) and 

(g)(4)(ii) of this AD should be further 

clarified to capture the commenter’s 

intent; therefore, we have changed those 

paragraphs 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. 

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 

68 products of U.S. registry. We also 

estimate that it will take about 5 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $27,200, or $400 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 

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 39–14896 (72 FR 

2612, January 22, 2007) and adding the 

following new AD: 

2008–17–02 Airbus: Amendment 39–15640. 

Docket No. FAA–2008–0406; Directorate 

Identifier 2007–NM–196–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 17, 2008. 

Affected ADs 

(b) The AD supersedes AD 2007–02–09, 

Amendment 39–14896. 

Applicability 

(c) This AD applies to Airbus Model A310 

airplanes, certificated in any category, all 

certified models, all serial numbers; except 

for those where LH (left-hand) and RH (righthand) wing MLG (main landing gear) rib 5 

forward lugs have been repaired by 

installation of oversized interference fit 

bushes as per Airbus A310 Repair Instruction 


hsrobinson on PROD1PC76 with RULES
47034 Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 

R572–49121, or which have had Airbus 

Service Bulletin A310–57–2090 (Airbus 

modification 13329) embodied in service. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During routine visual inspection, a crack 

has been found in the wing MLG (main 

landing gear) rib 5 forward attachment lug on 

two A310 in-service aircraft. Laboratory 

examination of one of the cracked ribs 

confirmed that the crack is due to the 

presence of pitting corrosion in the forward 

lug holes. Also on both aircraft medium to 

heavy corrosion was found in the forward 

lugs on the opposite wing after removal of 

the bushes. This situation if not detected, 

could affect the structural integrity of the 

MLG attachment. As an interim measure, 

Airbus published Alert Service Bulletin 

(ASB) A310–57A2088 to introduce a 

repetitive detailed visual inspection (DVI) of 

the forward attachment lug of MLG Rib 5. 

EASA issued Emergency Airworthiness 

Directive (EAD) 2006–0335–E [which 

corresponds to FAA AD 2007–02–09] to 

require the accomplishment of this repetitive 

DVI. 

In order to ensure the detection of any 

crack at an early stage in the forward lug of 

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

Rib 5 aft bearing attachment, the Type 

Certificate holder has developed a new 

inspection by means of ultrasonic method. 

For the reasons described above, this new 

inspection program is rendered mandatory by 

this AD, which cancels and replaces the 

requirement of EAD 2006–0335–E. 

The corrective action includes repairing or 

replacing MLG Rib 5, as applicable. 

Restatement of Requirements of AD 2007–

02–09 

(f) Unless already done, do the following 

actions specified in paragraphs (f)(1), (f)(2), 

and (f)(3) of this AD in accordance with the 

instructions defined in Airbus Service 

Bulletin A310–57A2088, dated November 6, 

2006. 

(1) Before the accumulation of 12,000 total 

flight cycles, or within 14 days after February 

6, 2007 (the effective date of AD 2007–02–

09), whichever occurs later: Perform a 

detailed visual inspection of the LH and RH 

wing MLG Rib 5 aft bearing forward lugs. 

(2) If any crack is detected at LH and/or RH 

aft bearing forward lug, contact Airbus and 

proceed with the replacement before next 

flight. 

(3) Repeat the inspection at intervals not 

exceeding 100 flight cycles. 

New Requirements of This AD: Actions and 

Compliance 

(g) Unless already done, before the 

accumulation of 12,000 total flight cycles or 

before the accumulation of 12,000 flight 

cycles on MLG Rib 5, or within 14 days after 

the effective date of this AD, whichever 

occurs latest: Perform either a detailed visual 

inspection (DVI) or an ultrasonic inspection 

of the LH and RH MLG Rib 5 aft bearing 

forward lug for cracks, in accordance with 

the instructions defined in Airbus Service 

Bulletin A310–57–2091, excluding Appendix 

01, dated May 22, 2007. If a MLG Rib 5 has 

been replaced on one side only, then the RH 

and LH must be considered separately. Doing 

this inspection ends the requirements of 

paragraph (f) for that MLG Rib 5 only. 

Note 1: The ultrasonic inspection will 

detect any crack at an early stage and will 

limit the risk of extensive repairs. This earlier 

crack detection is not possible with the DVI. 

(1) If no crack is detected during any 

inspection required by paragraph (g) of this 

AD: Repeat the applicable inspection at the 

time specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD. 

(i) Repeat the DVI thereafter at intervals not 

to exceed 100 flight cycles. 

(ii) Repeat the ultrasonic inspection 

thereafter at intervals not to exceed 825 flight 

cycles. 

(2) Replacement of the MLG Rib 5 bushes 

with new bushes with high interference fit in 

the aft bearing forward lugs of MLG Rib 5, 

in accordance with the instructions defined 

in Airbus Service Bulletin A310–57–2090, 

Revision 01, dated December 19, 2007, ends 

the repetitive inspections required by 

paragraph (g)(1) of this AD for that MLG Rib 

5 only. 

(3) If any crack is detected during the DVI 

required by paragraph (g) of this AD: Before 

further flight, contact Airbus for replacement 

instructions and replace the MLG Rib 5 

bushes before further flight. Repeat the 

applicable inspection in paragraph (g) of this 

AD at the time specified in paragraph (g)(1)(i) 

or (g)(1)(ii) of this AD. Accomplishing the 

replacement of the MLG Rib 5 bushes with 

new bushes with high interference fit in the 

aft bearing forward lugs of MLG Rib 5, in 

accordance with the instructions defined in 

Airbus Service Bulletin A310–57–2090, 

Revision 01, dated December 19, 2007, ends 

the repetitive inspections required by 

paragraph (g)(1) of this AD for that MLG Rib 

5 only. 

(4) If any crack is detected during the 

ultrasonic inspection required by paragraph 

(g) of this AD, before further flight, 

accomplish the actions specified in 

paragraph (g)(4)(i) or (g)(4)(ii) of this AD, as 

applicable. 

(i) If any crack is not visible on MLG Rib 

5: Before further flight, repair MLG Rib 5 

using Airbus A310 Repair Instruction R572–

49121, Issue C, dated May 2007. After 

embodiment of the repair instruction, no 

further actions are necessary as required by 

this AD and specified in Airbus Service 

Bulletin A310–57–2091, excluding Appendix 

01, dated May 22, 2007, for that MLG Rib 5 

only. 

(ii) If any crack is visible on MLG Rib 5: 

Before further flight, contact Airbus for rib 

replacement instructions, and replace before 

further flight. Repeat the applicable 

inspection in paragraph (g) of this AD at the 

time specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD. Accomplishing the 

replacement of the MLG Rib 5 bushes with 

new bushes with high interference fit in the 

aft bearing forward lugs of MLG Rib 5, in 

accordance with the instructions defined in 

Airbus Service Bulletin A310–57–2090, 

Revision 01, dated December 19, 2007, ends 

the repetitive inspections required by 

paragraph (g) of this AD for that MLG Rib 5 

only. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

(1) Although the MCAI or service 

information allows flight with cracks on aft 

bearing forward lugs for a certain period of 

time, this AD requires replacing MLG Rib 5 

before further flight if any crack is found. 

(2) Although the MCAI or service 

information specifies submitting an 

inspection report sheet to Airbus, this AD 

would not require that action. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Tom Stafford, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1622; fax (425) 227–1149. 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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2007–0195, 

dated July 19, 2007; and Airbus Service 

Bulletins A310–57–2090, Revision 01, dated 

December 19, 2007; and A310–57–2091, 

including Appendix 01, dated May 22, 2007; 

for related information. 

Material Incorporated by Reference 

(j) You must use the applicable service 

information specified in Table 1 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 


hsrobinson on PROD1PC76 with RULES
Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 47035 

TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE

Airbus service information Revision/issue level Date 

Service Bulletin A310–57A2088, excluding Appendix 01 ............................................................... Original ........................ November 6, 2006. 

Service Bulletin A310–57–2090 ...................................................................................................... 01 ................................ December 19, 2007. 

Service Bulletin A310–57–2091, excluding Appendix 01 ................................................................ Original ........................ May 22, 2007. 

A310 Repair Instruction R572–49121 ............................................................................................. C .................................. May 2007. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information specified in Table 2 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 2—NEW MATERIAL INCORPORATED BY REFERENCE

Airbus service information Revision/issue level Date 

Service Bulletin A310–57–2090 ...................................................................................................... 01 ................................ December 19, 2007. 

Service Bulletin A310–57–2091, excluding Appendix 01 ................................................................ Original ........................ May 22, 2007. 

A310 Repair Instruction R572–49121 ............................................................................................. C .................................. May 2007. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Airbus Service Bulletin A310–

57A2088, excluding Appendix 01, dated 

November 6, 2006, on February 6, 2007 (72 

FR 2612, January 22, 2007). 

(3) For service information identified in 

this AD, contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

(4) 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 July 31, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–18561 Filed 8–12–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0043; Directorate 

Identifier 2007–NM–058–AD; Amendment 

39–15632; AD 2008–16–14] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747SR, and 747SP 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Boeing Model 

747 series airplanes. That AD currently 

requires inspecting to detect cracking in 

certain lower lobe fuselage skin lap 

joints, doing repetitive inspections for 

cracking at certain fastener locations 

having countersunk fasteners, and 

replacing countersunk fasteners with 

protruding head fasteners at certain 

fastener locations. This new AD requires 

replacing a previous high-frequency 

eddy current (HFEC) inspection method 

with a new HFEC inspection method, 

adding a one-time inspection for 

cracking of certain airplanes, and 

terminating the adjustment factor for the 

inspection compliance times based on 

cabin differential pressure. This AD also 

requires inspecting additional lap joints. 

This AD results from reports of fuselage 

skin cracks found at certain countersunk 

fastener locations in the upper row of 

lap joints near the wing-to-body fairings, 

and from a report that the presence of 

Alodine-coated rivets could cause faulty 

results during the required inspections 

using the optional sliding probe HFEC 

inspection method specified in the 

existing AD. We are issuing this AD to 

prevent reduced structural integrity of 

the fuselage. 

DATES: This AD becomes effective 

September 17, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 17, 2008. 

On August 24, 1994 (59 FR 37659, 

July 25, 1994), the Director of the 

Federal Register approved the 

incorporation by reference of Boeing 

Service Bulletin 747–53A2312, 

including the ‘‘Addendum,’’ Revision 2, 

dated October 8, 1992. 

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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that supersedes AD 94–15–06, 

amendment 39–8977 (59 FR 37659, July 

25, 1994). The existing AD applies to 

certain Boeing Model 747 series 

airplanes. That supplemental NPRM 

was published in the Federal Register 

on May 7, 2008 (73 FR 25601). That 

supplemental NPRM proposed to 

continue to require inspecting to detect 

cracking in certain lower lobe fuselage 

skin lap joints, doing repetitive 


hsrobinson on PROD1PC76 with RULES