Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 3361 

by adding the following new 

airworthiness directive (AD): 

2007–02–14 Boeing: Amendment 39–14901. 

Docket No. FAA–2006–24691; 

Directorate Identifier 2006–NM–051–AD. 

Effective Date 

(a) This AD becomes effective March 1, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737–

600, –700, –700C, –800, and –900 series 

airplanes, certificated in any category; as 

identified in Boeing Special Attention 

Service Bulletin 737–28–1225, Revision 1, 

dated October 30, 2006. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent arcing or 

sparking in the fuel tank in the event of a 

lightning strike, which could result in an 

uncontrolled fire or explosion. 

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. 

Test, Inspection, and Corrective and Other 

Specified Actions 

(f) Within 60 months after the effective 

date of this AD, test the electrical resistance 

of the bond between the bulkhead fitting for 

the fuel feed line and the wing front spar on 

the left and right wings, do a general visual 

inspection of adjacent bonding jumpers to 

make sure they are installed correctly, and do 

all applicable corrective and other specified 

actions. Do all the actions in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–28–

1225, Revision 1, dated October 30, 2006. All 

applicable corrective actions and other 

specified actions must be done before further 

flight after the electrical resistance test. 

Credit for Actions Accomplished Previously 

(g) Actions done before the effective date 

of this AD in accordance with Boeing Special 

Attention Service Bulletin 737–28–1225, 

dated January 12, 2006; are considered 

acceptable for compliance with the actions 

required by paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Material Incorporated by Reference 

(i) You must use Boeing Special Attention 

Service Bulletin 737–28–1225, Revision 1, 

dated October 30, 2006, to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. The Director of 

the Federal Register approved the 

incorporation by reference of this document 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for a copy of this 

service information. You may review copies 

at the Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the 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 January 

11, 2007. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–898 Filed 1–24–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25271; Directorate 

Identifier 2006–NM–067–AD; Amendment 

39–14903; AD 2007–02–16] 

RIN 2120–AA64 

Airworthiness Directives; Saab Model 

SAAB-Fairchild SF340A (SAAB/ 

SF340A) and SAAB 340B 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 Saab Model 

SAAB-Fairchild SF340A and SAAB 

340B airplanes. That AD currently 

requires repetitive inspections for wear 

of the brushes and leads and for loose 

rivets of the direct current (DC) starter 

generator, and related investigative/ 

corrective actions if necessary. This new 

AD requires installing new, improved 

generator control units (GCUs). 

Installing the GCUs ends the repetitive 

inspection requirements of the existing 

AD. This AD results from reports of 

premature failures of the DC starter 

generator prior to scheduled overhaul. 

We are issuing this AD to prevent 

failure of the starter generator, which 

could cause a low voltage situation in 

flight and result in increased pilot 

workload and reduced redundancy of 

the electrical powered systems. 

DATES: This AD becomes effective 

March 1, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 1, 2007. 

On April 1, 2005 (70 FR 9215, 

February 25, 2005), the Director of the 

Federal Register approved the 

incorporation by reference of Saab 

Service Bulletin 340–24–035, dated July 

5, 2004, including Attachment 1 

(Goodrich Service Information Letter 

23080–03X–24–01), dated July 1, 2004. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Saab Aircraft AB, SAAB 

Aircraft Product Support, S–581.88, 

Linko ̈ping, Sweden, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Mike Borfitz, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2677; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

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

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2005–04–12, amendment 

39–13984 (70 FR 9215, February 25, 

2005). The existing AD applies to 

certain Saab Model SAAB-Fairchild 

SF340A and SAAB 340B airplanes. That 

NPRM was published in the Federal 

Register on July 6, 2006 (71 FR 38311). 

That NPRM proposed to continue to 

require repetitive inspections for wear 

of the brushes and leads and for loose 

rivets of the direct current (DC) starter 

generator, and related investigative/ 


ycherry on PROD1PC64 with RULES
3362 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 

corrective actions if necessary. That 

NPRM also proposed to require 

installing new, improved generator 

control units (GCUs), which would end 

the repetitive inspection requirements. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request To Change Incorporation of 

Certain Information 

The Modification and Replacement 

Parts Association (MARPA) states that, 

typically, airworthiness directives are 

based on service information originating 

with the type certificate holder or its 

suppliers. MARPA adds that 

manufacturer service documents are 

privately authored instruments 

generally having copyright protection 

against duplication and distribution. 

MARPA notes that when a service 

document is incorporated by reference 

into a public document, such as an 

airworthiness directive, it loses its 

private, protected status and becomes a 

public document. MARPA adds that if 

a service document is used as a 

mandatory element of compliance, it 

should not simply be referenced, but 

should be incorporated into the 

regulatory document; by definition, 

public laws must be public, which 

means they cannot rely upon private 

writings. MARPA is concerned that the 

failure to incorporate essential service 

information could result in a court 

decision invalidating the AD. 

MARPA adds that incorporated by 

reference service documents should be 

made available to the public by 

publication in the Docket Management 

System (DMS), keyed to the action that 

incorporates them. MARPA notes that 

the stated purpose of the incorporation 

by reference method is brevity, to keep 

from expanding the Federal Register 

needlessly by publishing documents 

already in the hands of the affected 

individuals; traditionally, ‘‘affected 

individuals’’ means aircraft owners and 

operators, who are generally provided 

service information by the 

manufacturer. MARPA adds that a new 

class of affected individuals has 

emerged, since the majority of aircraft 

maintenance is now performed by 

specialty shops instead of aircraft 

owners and operators. MARPA notes 

that this new class includes 

maintenance and repair organizations, 

component servicing and repair shops, 

parts purveyors and distributors, and 

organizations manufacturing or 

servicing alternatively certified parts 

under section 21.303 (parts 

manufacturer approval) (PMA) of the 

Federal Aviation Regulations (14 CFR 

part 21). MARPA adds that the concept 

of brevity is now nearly archaic as 

documents exist more frequently in 

electronic format than on paper. 

Therefore, MARPA asks that the service 

documents deemed essential to the 

accomplishment of the NPRM be 

incorporated by reference into the 

regulatory instrument, and published in 

the DMS. 

We understand MARPA’s comment 

concerning incorporation by reference. 

The Office of the Federal Register (OFR) 

requires that documents that are 

necessary to accomplish the 

requirements of the AD be incorporated 

by reference during the final rule phase 

of rulemaking. This final rule 

incorporates by reference the service 

information necessary for the 

accomplishment of the requirements 

mandated by this AD. Further, we point 

out that while documents that are 

incorporated by reference do become 

public information, they do not lose 

their copyright protection. For that 

reason, we advise the public to contact 

the manufacturer to obtain copies of the 

referenced service information. 

Additionally, we do not publish 

service documents in DMS. We are 

currently reviewing our practice of 

publishing proprietary service 

information. Once we have thoroughly 

examined all aspects of this issue, and 

have made a final determination, we 

will consider whether our current 

practice needs to be revised. However, 

we consider that to delay this AD action 

for that reason would be inappropriate, 

since we have determined that an 

unsafe condition exists and that the 

requirements in this AD must be 

accomplished to ensure continued 

safety. Therefore, we have not changed 

the AD in this regard. 

Request To Reference PMA Parts 

MARPA also states that type 

certificate holders in their service 

documents typically ignore the possible 

existence of PMA parts. MARPA states 

that this is particularly true with foreign 

manufacturers where the concept may 

not exist or be implemented in the 

country of origin. MARPA points out 

that the service document upon which 

an airworthiness directive is based 

frequently will require removing a 

certain part-numbered part and 

installing a different part-numbered part 

as a corrective action. According to 

MARPA, this runs afoul of part 21 of the 

Federal Aviation Regulations (14 CFR 

part 21), section 21.303, which permits 

the development, certification, and 

installation of alternatively certified 

parts. 

MARPA further states that installing a 

certain part-numbered part to the 

exclusion of all other parts is not a 

favored general practice. MARPA states 

that such an action has the dual effect 

of preventing, in some cases, the 

installation of a perfectly good part; 

while at the same time prohibiting the 

development of new parts permitted 

under § 21.303. According to MARPA, 

such a prohibition runs the risk of 

taking the AD out of the realm of safety 

and into the world of economics, since 

prohibiting the development, sale, and 

use of a perfectly airworthy part has 

noting to do with safety. MARPA states 

that courts could easily construe such 

actions as being outside the statutory 

basis of the AD (safety) and, as such, 

unenforceable. MARPA adds that courts 

are reluctant to find portions of a rule 

unenforceable since they lack the 

knowledge and authority to re-write 

requirements, and are thus generally 

inclined to simply void the entire rule. 

In response to the commenter’s 

statement regarding running afoul of 

part 21 of the Federal Aviation 

Regulations (14 CFR part 21, under 

which the FAA issues PMAs, this 

statement appears to reflect a 

misunderstanding of the relationship 

between ADs and the certification 

procedural regulations of 14 CFR part 

21. Those regulations, including 

§ 21.303, are intended to ensure that 

aeronautical products comply with the 

applicable airworthiness standards. But 

ADs are issued when, notwithstanding 

those procedures, we become aware of 

unsafe conditions in these products or 

parts. Therefore, an AD takes 

precedence over design approvals when 

we identify an unsafe condition, and 

mandating installation of a certain part 

number in an AD is not at variance with 

§ 21.303. 

The AD provides a means of 

compliance for operators to ensure that 

the identified unsafe condition is 

addressed appropriately. For an unsafe 

condition attributable to a part, the AD 

normally identifies the replacement 

parts necessary to obtain that 

compliance. As stated in § 39.7 of the 

Federal Aviation Regulations (14 CFR 

39.7), ‘‘Anyone who operates a product 

that does not meet the requirements of 

an applicable airworthiness directive is 

in violation of this section.’’ Unless an 

operator obtains approval for an AMOC, 

replacing a part with one not specified 

by the AD would make the operator 

subject to an enforcement action and 

result in a civil penalty. No change to 

the AD is necessary in this regard. 


ycherry on PROD1PC64 with RULES
Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 3363 

Request to Stop Using Alternative 

Method of Compliance (AMOC) 

MARPA also believes that the practice 

of requiring an AMOC to install a PMA 

part should be stopped. MARPA states 

that this is somehow tantamount to 

stating, illogically, that all PMA parts 

are inherently defective and require an 

additional layer of approval when the 

original equipment manufacturer (OEM) 

part is determined to be defective. 

MARPA suspects that the FAA 

personnel who labored diligently to 

certify the PMA part might disagree 

with such a narrow, OEM-slanted view. 

MARPA states that if the PMA part is 

defective, then it must be deemed so in 

the AD, and not simply implied by a 

catch-all AMOC requirement. MARPA 

states that this is why it has repeatedly 

requested that we adopt language to trap 

such defective parts, and suggests that 

the FAA’s Transport Airplane 

Directorate adopt the language used by 

the Small Airplane Directorate to 

accomplish this. 

We infer that MARPA would like the 

AD to permit installation of any 

equivalent PMA parts so that it is not 

necessary for an operator to request 

approval of an AMOC in order to install 

an ‘‘equivalent’’ PMA part. Whether an 

alternative part is ‘‘equivalent’’ in 

adequately resolving the unsafe 

condition can only be determined on a 

case-by-case basis based on a complete 

understanding of the unsafe condition. 

The Transport Airplane Directorate’s 

policy is that, in order for operators to 

replace a part with one that is not 

specified in the AD, they must request 

an AMOC. This is necessary so that we 

can make a specific determination that 

an alternative part is or is not 

susceptible to the same unsafe 

condition. 

Request for Compliance With FAA 

Order 8040.2/Agreement on Parts 

Replacement 

MARPA points out that this AD, as 

written, does not comply with proposed 

FAA Order 8040.2 (AD Process for 

Mandatory Continuing Airworthiness 

Information (MCAI)), which states in the 

PMA section: ‘‘MCAI that require 

replacement or installation of certain 

parts could have replacement parts 

approved under part 21 of the Federal 

Aviation Regulations (14 CFR part 21), 

section 21.303, based on a finding of 

identicality. We have determined that 

any parts approved under this 

regulation and installed should be 

subject to the actions of our AD and 

included in the applicability of our 

AD.’’ MARPA points out that the Small 

Airplane Directorate has developed a 

blanket statement that resolves this 

issue. The statement includes words 

similar to that in the proposed Order 

8040.2. 

The FAA recognizes the need for 

standardization on the issue of 

addressing PMA parts in ADs, and 

currently is in the process of reviewing 

it at the national level. The Transport 

Airplane Directorate considers that to 

delay this particular AD action would 

be inappropriate, since we have 

determined that an unsafe condition 

exists and that replacement of certain 

parts must be accomplished to ensure 

continued safety. Therefore, no change 

has been made to the final rule in this 

regard. 

The NPRM did not address PMA 

parts, as provided in draft FAA Order 

8040.2, because the Order was only a 

draft that was out for comment at the 

time. After issuance of the NPRM, the 

Order was revised and issued as FAA 

Order 8040.5 with an effective date of 

September 29, 2006. FAA Order 8040.5 

does not address PMA parts in ADs. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

This AD affects about 170 airplanes of 

U.S. registry. 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 

Parts Cost per airplane Fleet cost 

Inspections (required by AD 2005–04–12) ......... 1 $80 $0 $80, per inspection 

cycle.

$13,600, per inspection 

cycle. 

Installation (new action) ...................................... 1 80 7,598 $7,678 .......................... $1,305,260. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 


ycherry on PROD1PC64 with RULES
3364 Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–13984 (70 

FR 9215, February 25, 2005) and by 

adding the following new airworthiness 

directive (AD): 

2007–02–16 Saab Aircraft AB: 

39–14903. Docket No. FAA–2006–25271; 

Directorate Identifier 2006–NM–067–AD. 

Effective Date 

(a) This AD becomes effective March 1, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2005–04–12. 

Applicability 

(c) This AD applies to Saab Model SAABFairchild SF340A (SAAB/SF340A) airplanes 

having serial numbers 004 through 159 

inclusive, and Model SAAB 340B airplanes 

having serial numbers 160 through 367 

inclusive; certificated in any category; on 

which Saab Modification 2533 has not been 

implemented. 

Unsafe Condition 

(d) This AD results from reports of 

premature failures of the direct current (DC) 

starter generator prior to scheduled overhaul. 

We are issuing this AD to prevent failure of 

the starter generator, which could cause a 

low voltage situation in flight and result in 

increased pilot workload and reduced 

redundancy of the electrical powered 

systems. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of the Requirements of AD 

2005–04–12 

Inspections for Wear of the DC Starter 

Generator Brushes and Leads 

(f) For generators overhauled in accordance 

with Maintenance Review Board (MRB) Task 

243104: Before 800 flight hours since last 

overhaul, or within 100 flight hours after 

April 1, 2005 (the effective date of AD 2005–

04–12), perform a general visual inspection 

for wear of the DC starter generator brushes 

and leads, in accordance with Saab Service 

Bulletin 340–24–035, dated July 5, 2004. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Note 2: Saab Service Bulletin 340–24–035, 

dated July 5, 2004, references Goodrich 

Service Information Letter 23080–03X–24–

01, dated July 1, 2004, as an additional 

source of service information. 

(1) If the tops of the brush sets are above 

the top of the brush box, repeat the 

inspection thereafter at intervals not to 

exceed 800 flight hours until paragraph (i) of 

this AD is done. 

(2) If the tops of the brush sets are below 

the top of the brush box, before further flight, 

measure the brushes and determine the 

amount of brush life remaining, in 

accordance with the service bulletin. 

(i) If the brush wear is within the limits 

specified in the service bulletin, repeat the 

inspection thereafter at intervals not to 

exceed 800 flight hours until paragraph (i) of 

this AD is done. 

(ii) If the brush wear is outside the limits 

specified in the service bulletin, before 

further flight, replace the starter generator 

with a new or serviceable starter generator, 

in accordance with the service bulletin. 

Inspections for Loose Rivets 

(g) For generators overhauled in 

accordance with MRB Task 243104: Before 

800 flight hours since last overhaul, or within 

100 flight hours after April 1, 2005, 

whichever occurs later, perform a general 

visual inspection of each leading wafer brush 

for loose rivets, in accordance with Saab 

Service Bulletin 340–24–035, dated July 5, 

2004. Repeat the inspection thereafter at 

intervals not to exceed 800 flight hours until 

paragraph (i) of this AD is done. If any rivet 

is loose, before further flight, replace the DC 

starter generator with a new or serviceable 

starter generator, in accordance with the 

service bulletin. 

MRB Task 243103 or 243101 

(h) For generators overhauled or with 

brush replacement accomplished in 

accordance with MRB Task 243103 or 

243101, no action is required by paragraphs 

(f) and (g) of this AD. 

New Requirements of This AD 

Installation 

(i) For all generators: Within 36 months 

after the effective date of this AD, install new 

improved generator control units (GCUs) in 

accordance with the Accomplishment 

Instructions of Saab Service Bulletin 340–24–

026, Revision 03, dated December 20, 2004. 

Installing the GCUs terminates the repetitive 

inspection requirements of paragraphs (f) and 

(g) of this AD. 

Alternative Methods of Compliance (AMOCs) 

(j)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(k) Swedish airworthiness directive 1–197, 

effective November 5, 2004, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(l) You must use Saab Service Bulletin 

340–24–026, Revision 03, dated December 

20, 2004; and Saab Service Bulletin 340–24–

035, dated July 5, 2004, including 

Attachment 1 (Goodrich Service Information 

Letter 23080–03X–24–01), dated July 1, 2004; 

as applicable; to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Saab Service Bulletin 340–24–026, Revision 

03, dated December 20, 2004, in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) On April 1, 2005 (70 FR 9215, February 

25, 2005), the Director of the Federal Register 

approved the incorporation by reference of 

Saab Service Bulletin 340–24–035, dated July 

5, 2004, including Attachment 1 (Goodrich 

Service Information Letter 23080–03X–24–

01), dated July 1, 2004. 

(3) Contact Saab Aircraft AB, SAAB 

Aircraft Product Support, S–581.88, 

Linko$ping, Sweden, for a copy of this 

service information. You may review copies 

at the Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., Room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the 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 January 

11, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–901 Filed 1–24–07; 8:45 am] 

BILLING CODE 4910–13–P 


ycherry on PROD1PC64 with RULES