Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 12249 

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: 

2009–09–22 Airbus: Amendment 39–15859. 

Docket No. FAA–2008–1327; Directorate 

Identifier 2008–NM–161–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 28, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A318– 

111, –112, –121, and –122; A319–111, –112, 

–113, –114, –115, –131, –132, and –133; 

A320–111, –211, –212, –214, –231, –232, 

–233; and A321–111, –112, –131, –211, –212, 

–213, –231, and –232 series airplanes; 

certificated in any category; equipped with a 

cockpit door latch/striker assembly having 

part number AR4714–1 or AR4714–3. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 25: Equipment/furnishings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

An A320 aircraft experienced an event 

where it was not possible to open the 

reinforced cockpit door, even after power had 

been removed from the aircraft. Investigation 

has identified that the cockpit door latch/ 

striker assembly may have overheated, 

causing permanent internal damage prior to 

being electrically isolated by the internal 

thermal fuse. This condition, in case of a 

rapid decompression in the cockpit, would 

prevent the necessary unlocking/opening of 

the door, which may lead to failure of the 

airplane structure. 

To prevent this, an improved strike 

package/door bolting system, including a 

Polymer Positive Temperature Coefficient 

(PPTC) element (overheat protection) was 

introduced by Airbus Modification 35219 in 

production and modification 35218 (Service 

Bulletin A320–25–1444) in-service. The 

PPTC is a resettable thermistor and is 

installed on the frame of the electricallyoperated cockpit door latch/striker assembly. 

The in-service implementation of this 

modification was originally managed by an 

Airbus campaign but the rate of installation 

by operators has not met the expected 

timescales, making mandatory action 

necessary to address this. 

For the reasons described above, this AD 

requires the installation of improved cockpit 

door latch/striker assemblies. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 8 months after the effective date 

of this AD: Replace all cockpit door latch/ 

striker assemblies having part number 

AR4714–1 or AR4714–3 with modified units 

in accordance with Airbus Service Bulletin 

A320–25–1444, Revision 02, dated August 1, 

2006 (Airbus Modification 35218). 

(2) Previous accomplishment of the 

replacement before the effective date of this 

AD in accordance with Airbus Service 

Bulletin A320–25–1444, dated April 29, 

2005; or Revision 01, dated July 19, 2005; 

meets the requirements of paragraph (f)(1) of 

this AD. 

FAA AD Differences 

Note 1: 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, 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: Tim Dulin, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2141; 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 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2008– 

0151, dated August 5, 2008; and Airbus 

Service Bulletin A320–25–1444, Revision 02, 

dated August 1, 2006; for related information. 

Material Incorporated by Reference 

(i) You must use Airbus Service Bulletin 

A320–25–1444, Revision 02, dated August 1, 

2006 to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 

12, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–5959 Filed 3–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1043; Directorate 

Identifier 2008–NM–036–AD; Amendment 

39–15845; AD 2009–06–09] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH Dornier Model 328–100 

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: 

During overhaul on a Dornier 328–100 

landing gear unit, parts of the MLG (main 

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12250 Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 

landing gear) main body and trailing arm 

bushings have been found corroded. 

Investigation showed that over time, these 

bushings can migrate, creating the risk of 

corrosion in adjacent areas. Such corrosion, 

if not detected, could cause damage to the 

MLG, possibly resulting in MLG functional 

problems or failure. 

* * * * * 

Functional problems or failure of the 

MLG could result in the inability of the 

MLG to extend or retract. We are issuing 

this AD to require actions to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective April 

28, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 28, 2009. 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2125; 

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 September 30, 2008 (73 FR 

56763). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During overhaul on a Dornier 328–100 

landing gear unit, parts of the MLG (main 

landing gear) main body and trailing arm 

bushings have been found corroded. 

Investigation showed that over time, these 

bushings can migrate, creating the risk of 

corrosion in adjacent areas. Such corrosion, 

if not detected, could cause damage to the 

MLG, possibly resulting in MLG functional 

problems or failure. 

Based on these findings, the existing 

mandatory retrofit limitation (as required by 

Airworthiness Limitations Document under 

Section E ‘‘Mandatory Retrofit Items’’ since 

16 September 1998) for the MLG bushings at 

15,000 FC (flight cycles) has been amended 

with ‘‘* * * or 6 calendar years time-inservice (TIS), whichever occurs first’’. 

For the reasons described above, this 

[EASA] Airworthiness Directive requires the 

implementation of the revised mandatory 

retrofit limitation and modification of MLG 

bushings that have exceeded the new limit. 

Functional problems or failure of the 

MLG could result in the inability of the 

MLG to extend or retract. 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 comment received from 

the commenter. 

Request To Clarify Certain Language 

The commenter, Patrick Brady, has a 

concern about proposed language in the 

compliance section that may lead to 

confusion for operators. The commenter 

asks that paragraph (f)(1)(ii) of the 

NPRM be changed to clarify that the 

requirement for replacing the bushings 

is applicable only to bushings that were 

installed before issuance of Dornier 

Service Bulletin SB–328–32–245, 

Revision 2, dated November 21, 2007; 

and Messier-Dowty Service Bulletin 

800–32–014, Revision 1, dated July 19, 

1999. The commenter adds that if the 

bushings were replaced in accordance 

with the referenced service bulletins, 

and bushings with post-service bulletin 

part numbers were installed, no 

additional requirement to replace the 

bushings should be imposed. 

We agree that further clarification is 

necessary; however, we do not agree 

that it is necessary to change the 

language specified in paragraph (f)(1)(ii) 

of this AD. If new bushings with postservice bulletin part numbers were 

installed in accordance with Dornier 

Service Bulletin SB–328–32–245, 

Revision 2, dated November 21, 2007; 

and Messier-Dowty Service Bulletin 

800–32–014, Revision 1, dated July 19, 

1999; and a records check has been 

done which verifies that the bushings 

were replaced with new bushings, there 

is no requirement in this AD to replace 

those bushings. In addition, paragraph 

(f) of the AD specifies to do the actions 

‘‘unless already done.’’ We have made 

no change to the AD in this regard. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 

13 products of U.S. registry. We also 

estimate that it will take about 28 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $10,000 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$159,120, or $12,240 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; 

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Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 12251 

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: 

2009–06–09 328 Support Services GMBH 

(Formerly, AvCraft Aerospace GmbH, 

Formerly Fairchild Dornier GmbH, 

Formerly Dornier Luftfahrt GmbH): 

Amendment 39–15845. Docket No. 

FAA–2008–1043; Directorate Identifier 

2008–NM–036–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 28, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 328 Support 

Services GmbH Dornier Model 328–100 

airplanes, all serial numbers, certificated in 

any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During overhaul on a Dornier 328–100 

landing gear unit, parts of the MLG (main 

landing gear) main body and trailing arm 

bushings have been found corroded. 

Investigation showed that over time, these 

bushings can migrate, creating the risk of 

corrosion in adjacent areas. Such corrosion, 

if not detected, could cause damage to the 

MLG, possibly resulting in MLG functional 

problems or failure. 

Based on these findings, the existing 

mandatory retrofit limitation (as required by 

Airworthiness Limitations Document under 

Section E ‘‘Mandatory Retrofit Items’’ since 

16 September 1998) for the MLG bushings at 

15,000 FC (flight cycles) has been amended 

with ‘‘* * * or 6 calendar years time-inservice (TIS), whichever occurs first’’. 

For the reasons described above, this 

[EASA] Airworthiness Directive requires the 

implementation of the revised mandatory 

retrofit limitation and modification of MLG 

bushings that have exceeded the new limit. 

Functional problems or failure of the MLG 

could result in the inability of the MLG to 

extend or retract. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Modify the MLG main body and trailing 

arm bushings at the applicable time specified 

in paragraph (f)(1)(i) or (f)(1)(ii) of this AD, 

or within 12 months after the effective date 

of this AD, whichever occurs later. Do the 

modification in accordance with the 

instructions of Dornier Service Bulletin SB– 

328–32–245, Revision 2, dated November 21, 

2007; and Messier-Dowty Service Bulletin 

800–32–014, Revision 1, dated July 19, 1999. 

(i) For airplanes on which the bushings 

have not been replaced as of the effective 

date of this AD: Before the MLG accumulates 

15,000 flight cycles or 6 years, whichever 

occurs first. 

(ii) For airplanes on which the bushings 

have been replaced as of the effective date of 

this AD: Before the MLG exceeds 15,000 

flight cycles or 6 years after replacement of 

the bushings, whichever occurs first. 

(2) Within 1 month after the effective date 

of this AD: Revise the Airworthiness 

Limitations (AWL) section of the Instructions 

for Continued Airworthiness by 

incorporating the information in Dornier 328 

Temporary Revision (TR) ALD–084, dated 

November 7, 2005, into Section E, 

‘‘Mandatory Retrofit Items’’ of the Dornier 

328 Airworthiness Limitations Document 

(ALD). 

Note 1: The actions required by paragraph 

(f)(2) of this AD may be done by inserting a 

copy of Dornier 328 TR ALD–084, dated 

November 7, 2005, into Section E of the 

Dornier 328 ALD. 

(3) After doing the replacement required by 

paragraph (f)(1) of this AD, no person may 

install, on any airplane, a MLG unit as a 

replacement part, unless it has been modified 

in accordance with paragraph (f)(1) of this 

AD. 

FAA AD Differences 

Note 2: 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, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to Attn: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; 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 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2008– 

0009, dated January 11, 2008; Messier-Dowty 

Service Bulletin 800–32–014, Revision 1, 

dated July 19, 1999; Dornier Service Bulletin 

SB–328–32–245, Revision 2, dated November 

21, 2007; and Dornier 328 TR ALD–084, 

dated November 7, 2005, to the Dornier 328 

Airworthiness Limitations Document; for 

related information. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 1 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. 

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12252 Federal Register / Vol. 74, No. 55 / Tuesday, March 24, 2009 / Rules and Regulations 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Dornier 328 Temporary Revision ALD–084 to the Dornier 328 Airworthiness Limitations Document.Original .............................................. November 7, 2005. 

Dornier Service Bulletin SB–328–32–245 ...................................................... 2 ......................................................... November 21, 2007. 

Messier-Dowty Service Bulletin 800–32–014 ................................................. 1 ......................................................... July 19, 1999. 

Messier-Dowty Service Bulletin 800–32– 

014, Revision 1, dated July 19, 1999, contains 

the following effective pages: 

Page Nos. Revision level shown on page Date shown on page 

1, 6–8, 10, 12 ................................................................... 1 ....................................................................................... July 19, 1999. 

2–5, 9, 11, 13, 14 ............................................................. Original ............................................................................ January 18, 1999. 

(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 Dornier service information 

identified in this AD, contact 328 Support 

Services GmbH, Global Support Center, P.O. 

Box 1252, D–82231 Wessling, Federal 

Republic of Germany; telephone +49 8153 

88111 6666; fax +49 8153 88111 6565; e-mail 

gsc.op@328support.de; Internet http:// 

www.328support.de. 

(3) For Messier-Dowty service information 

identified in this AD, contact Messier 

Services Americas, Customer Support Center, 

45360 Severn Way, Sterling, Virginia 20166– 

8910; telephone 703–450–8233; fax 703–404– 

1621; Internet https:// 

techpubs.services.messier-dowty.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on February 

27, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–5955 Filed 3–23–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25390; Directorate 

Identifier 2005–NM–224–AD; Amendment 

39–15844; AD 2009–06–08] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 767 airplanes. This AD 

requires repetitive inspections for 

cracking of the wing skin, and related 

investigative/corrective actions if 

necessary. This AD results from reports 

of cracks found in the lower wing skin 

originating at the forward tension bolt 

holes of the aft pitch load fitting. We are 

issuing this AD to detect and correct 

cracking in the lower wing skin for the 

forward tension bolt holes at the aft 

pitch load fitting, which could result in 

a fuel leak and reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective April 

28, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 28, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207; 

telephone 206–544–9990; fax 206–766– 

5682; e-mail DDCS@boeing.com; 

Internet https:// 

www.myboeingfleet.com. 

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: 

Tamara Anderson, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917-6421; 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 would apply to certain Boeing 

Model 767 airplanes. That supplemental 

NPRM was published in the Federal 

Register on May 23, 2008 (73 FR 30009). 

That supplemental NPRM proposed to 

require repetitive inspections for 

cracking of the wing skin, and related 

investigative/corrective actions if 

necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the Supplemental NPRM 

Boeing concurs with the contents of 

the proposed rule. 

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