Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 47029 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

Tom Groves, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057–

3356; telephone (425) 227–1503; fax (425) 

425–1149. 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. 

Related Information 

(k) EASA airworthiness directive 2006–

0197 [Corrected], dated July 11, 2006, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(l) You must use the service information 

specified in Table 2 of this AD to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Service information Revision level Date 

AvCraft Service Bulletin SB–328–00–445, including Price Information Sheet ............................. Original ........................ August 23, 2004. 

AvCraft Service Bulletin SB–328–00–445 ..................................................................................... 1 .................................. June 17, 2005. 

Dornier Temporary Revision ALD–080 .......................................................................................... Original ........................ October 15, 2003. 

Section F, ‘‘Fuel Tank System Limitations,’’ of Dornier 328 Airworthiness Limitations Document 15 ................................ January 15, 2005. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

AvCraft Service Bulletin SB–328–00–445, 

Revision 1, dated June 17, 2005; and Section 

F, ‘‘Fuel Tank System Limitations,’’ of 

Dornier 328 Airworthiness Limitations 

Document, Revision 15, dated January 15, 

2005; in accordance with 5 U.S.C. 552(a) and 

1 CFR part 51. 

(2) On July 29, 2005 (70 FR 36470, June 24, 

2005), the Director of the Federal Register 

approved the incorporation by reference of 

AvCraft Service Bulletin SB–328–00–445, 

including Price Information Sheet, dated 

August 23, 2004; and Dornier Temporary 

Revision ALD–080, dated October 15, 2003. 

(3) Contact 328 Support Services GmbH, 

P.O. Box 1252, D–82231 Wessling, Federal 

Republic of Germany, 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/ibr-locations.html. 

Issued in Renton, Washington, on July 29, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–18425 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–2008–0179; Directorate 

Identifier 2007–NM–367–AD; Amendment 

39–15572; AD 2008–13–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–102, DHC–8–103, DHC–

8–106, DHC–8–201, DHC–8–202, DHC–

8–301, DHC–8–311, and DHC–8–315 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

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: 

Bombardier Aerospace has completed a 

system safety review of the aircraft fuel 

system against fuel tank safety standards 

* * *. 

[A]ssessment showed that supplemental 

maintenance tasks [inspections of fuel tank 

bonding jumpers, wiring harnesses, and 

drain valve components, among other items 

and actions; and applicable corrective 

actions] are required to prevent potential 

ignition sources within the fuel system, 

which could result in a fuel tank explosion. 

* * * 

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. 

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: 

Rocco Viselli, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7331; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 

That supplemental NPRM was 

published in the Federal Register on 

May 1, 2008 (73 FR 23995). That 

supplemental NPRM proposed to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Bombardier Aerospace has completed a 

system safety review of the aircraft fuel 

system against fuel tank safety standards 

introduced in Chapter 525 of the 

Airworthiness Manual through Notice of 

Proposed Amendment (NPA) 2002–043. The 

identified non-compliances were then 

assessed using Transport Canada Policy 

Letter No. 525–001, to determine if 

mandatory corrective action is required. 

The assessment showed that supplemental 

maintenance tasks [inspections of fuel tank 

bonding jumpers, wiring harnesses, and 

drain valve components, among other items 

and actions; and applicable corrective 

actions] are required to prevent potential 

ignition sources within the fuel system, 

which could result in a fuel tank explosion. 

Revisions have been made to Part 2 

‘‘Airworthiness Limitations List’’ of the 


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47030 Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 

DHC–8 Maintenance Program Manuals to 

introduce the required maintenance tasks. 

The corrective action is revising the 

Airworthiness Limitations Section of 

the Instructions for Continued 

Airworthiness to incorporate new 

limitations for fuel tank systems. 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 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Clarification of Identity of Model DHC–

8–201 Airplanes 

We have clarified the identity of 

certain airplanes as listed in the 

supplemental NPRM by correctly 

identifying them throughout this AD as 

Model DHC–8–201 airplanes. 

Removal of Reference to ‘‘a Later 

Revision’’ of Certain Maintenance 

Program Manuals (MPMs) 

We removed the reference to ‘‘a later 

revision of Part 2 ‘Airworthiness 

Limitations List’ of the applicable de 

Havilland Dash 8 Series MPM’’ from 

paragraph (f)(4) of this AD and removed 

Table 3 of the NPRM, which listed the 

MPMs (and renumbered the subsequent 

table accordingly). We removed the 

reference to the use of ‘‘later revisions’’

of the applicable service information 

from this AD to be consistent with FAA 

policy. This change will not increase the 

economic burden on any operator, nor 

will it increase the scope of the AD, 

since operators may request approval to 

use a later revision of the referenced 

service information as an alternative 

method of compliance, under the 

provisions of paragraph (g) of this AD. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 122 products of U.S. registry. We 

also estimate that it will take about 1 

work-hour 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 $9,760, or $80 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 adding 

the following new AD: 

2008–13–09 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–15572. 

Docket No. FAA–2008–0179; Directorate 

Identifier 2007–NM–367–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 17, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Bombardier 

Model DHC–8–102, DHC–8–103, DHC–8–

106, DHC–8–201, DHC–8–202, DHC–8–301, 

DHC–8–311, and DHC–8–315 airplanes, 

certificated in any category, all serial 

numbers. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (g) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 


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Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 47031 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Bombardier Aerospace has completed a 

system safety review of the aircraft fuel 

system against fuel tank safety standards 

introduced in Chapter 525 of the 

Airworthiness Manual through Notice of 

Proposed Amendment (NPA) 2002–043. The 

identified non-compliances were then 

assessed using Transport Canada Policy 

Letter No. 525–001, to determine if 

mandatory corrective action is required. 

The assessment showed that supplemental 

maintenance tasks [inspections of fuel tank 

bonding jumpers, wiring harnesses, and 

drain valve components, among other items 

and actions; and applicable corrective 

actions] are required to prevent potential 

ignition sources within the fuel system, 

which could result in a fuel tank explosion. 

Revisions have been made to Part 2 

‘‘Airworthiness Limitations List’’ of the 

DHC–8 Maintenance Program Manuals to 

introduce the required maintenance tasks. 

The corrective action is revising the 

Airworthiness Limitations Section (ALS) of 

the Instructions for Continued Airworthiness 

to incorporate new limitations for fuel tank 

systems. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 60 days after the effective date 

of this AD, or before December 16, 2008, 

whichever occurs first, revise the ALS of the 

Instructions for Continued Airworthiness to 

incorporate the fuel system limitations tasks 

identified in the de Havilland temporary 

revisions (TRs) to Part 2, ‘‘Airworthiness 

Limitations List,’’ of the Dash 8 Series 

Maintenance Program Manuals (‘‘the 

MPMs’’). The TRs are listed in Table 1 of this 

AD. For the tasks identified in the TRs, the 

initial compliance times start at the later of 

the applicable ‘‘Threshold’’ and ‘‘Grace 

Period’’ times specified in Table 2 of this AD, 

and the repetitive limitation tasks must be 

accomplished thereafter at the interval 

specified in the TRs, except as provided by 

paragraphs (f)(2), (f)(3), (f)(4), and (g)(1) of 

this AD. 

TABLE 1—TEMPORARY REVISIONS

Model de Havilland TR MPM 

DHC–8–102, DHC–8–103, and DHC–8–106 airplanes.AWL–110, dated August 31, 2007 .................. Dash 8 Series 100 MPM, Product Support 

Manual (PSM) 1–8–7, Part 2, ‘‘Airworthiness Limitations List’’. 

DHC–8–201, and DHC–8–202 airplanes ........... AWL 2–43, dated August 31, 2007 ................. Dash 8 Series 200 MPM, PSM 1–82–7, Part 

2, ‘‘Airworthiness Limitations List’’. 

DHC–8–301, DHC–8–311, and DHC–8–315 airplanes.AWL 3–109, dated August 31, 2007 ............... Dash 8 Series 300 MPM, PSM 1–83–7, Part 

2, ‘‘Airworthiness Limitations List’’. 

TABLE 2—INITIAL INSPECTIONS

Description 

Compliance time 

(whichever occurs later) 

Threshold Grace period 

Tasks with 6,000 flight hours/36 month intervals Before the accumulation of 6,000 total flight 

hours, or within 36 months since new, 

whichever occurs first.

Within 2,000 flight hours or 12 months after 

the effective date of this AD, whichever occurs first. 

Tasks with 18,000 flight hours/108 month intervals.Before the accumulation of 18,000 total flight 

hours, or within 108 months since new, 

whichever occurs first.

Within 6,000 flight hours or 36 months after 

the effective date of this AD, whichever occurs first. 

Tasks with 72,000 flight hours/36 year intervals Before the accumulation of 72,000 total flight 

hours, or within 36 years since new, whichever occurs first.

Within 600 flight hours or 3 months after the 

effective date of this AD, whichever occurs 

first. 

Note 2: The actions required by paragraph 

(f)(1) of this AD may be done by inserting a 

copy of the applicable TR listed in Table 1 

of this AD into the ALS of the applicable 

MPM listed in Table 1 of this AD. When the 

applicable TR has been included in general 

revisions of the applicable MPM, the general 

revisions may be inserted in the MPM, 

provided the relevant information in the 

general revision is identical to that in the 

applicable TR. 

(2) For those tasks with 6,000 flight hours/ 

36 month limitation task intervals: For 

airplanes that have accumulated 4,000 total 

flight hours or more, or 24 months or more 

since new, as of the effective date of this AD, 

do the initial limitation tasks within 2,000 

flight hours or 12 months after the effective 

date of this AD, whichever occurs first. 

Thereafter, repeat the limitation tasks at 

intervals not to exceed 6,000 flight hours or 

36 months, whichever occurs first. 

(3) For those tasks with 18,000 flight 

hours/108 month limitation task intervals: 

For airplanes that have accumulated 12,000 

total flight hours or more, or 72 months or 

more since new, as of the effective date of 

this AD, do the initial limitation tasks within 

6,000 flight hours or 36 months after the 

effective date of this AD, whichever occurs 

first. Thereafter, repeat the limitation tasks at 

intervals not to exceed 18,000 flight hours or 

108 months, whichever occurs first. 

(4) After accomplishing the actions 

specified in paragraphs (f)(1), (f)(2), and (f)(3) 

of this AD, no alternative inspections/ 

limitation tasks or inspection/limitation task 

intervals may be used unless the inspections/ 

limitation tasks or inspection/limitation task 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (g)(1) of this AD. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

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: Rocco Viselli, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–171, 

FAA, New York Aircraft Certification Office, 

1600 Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228–7331; 

fax (516) 794–5531. 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 


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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 


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