Federal Register / Vol. 73, No. 197 / Thursday, October 9, 2008 / Rules and Regulations 59493 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita Aircraft 

Certification Office (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: Erik 

Brown, Aerospace Engineer, Wichita ACO, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–4132; 

fax: (316) 946–4107. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

Material Incorporated by Reference 

(g) You must use Hawker Beechcraft 

Mandatory Service Bulletin SB 21–3899, 

original issue, dated May 2008, 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 Hawker Beechcraft 

Corporation, P.O. Box 85, Wichita, Kansas 

67201–0085; telephone: (800) 429–5372 or 

(316) 676–3140; http:// 

pubs.hawkerbeechcraft.com. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

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

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

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on 

September 30, 2008. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–23643 Filed 10–8–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0357; Directorate 

Identifier 2008–NM–005–AD; Amendment 

39–15687; AD 2008–21–03] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–300, –400, and –500 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Boeing Model 737–300, –400, and –500 

series airplanes. This AD requires 

repetitive inspections for discrepancies 

of the fuse pins of the inboard and 

outboard midspar fittings of the nacelle 

strut, and corrective actions if 

necessary. This AD results from a report 

of corrosion damage of the chrome 

runout on the head side found on all 

four midspar fuse pins of the nacelle 

strut. Additionally, a large portion of the 

chrome plate was missing from the 

corroded area of the shank. We are 

issuing this AD to detect and correct 

discrepancies of the fuse pins of the 

inboard and outboard midspar fittings of 

the nacelle strut, which could result in 

reduced structural integrity of the fuse 

pins and consequent loss of the strut 

and separation of the engine from the 

airplane. 

DATES: This AD is effective November 

13, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 13, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6432; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

Part 39 to include an airworthiness 

directive (AD) that would apply to all 

Boeing Model 737–300, –400, and –500 

series airplanes. That NPRM was 

published in the Federal Register on 

March 26, 2008 (73 FR 15959). That 

NPRM proposed to require repetitive 

inspections for discrepancies of the fuse 

pins of the inboard and outboard 

midspar fittings of the nacelle strut, and 

corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Support for the NPRM 

Boeing supports the NPRM. 

Deutsche Lufthansa (DLH) states that 

during inspections done per the AMM, 

for which the left- and right-hand 

pylons have to be removed, it observed 

several instances of corrosion or 

damaged chrome plating of the midspar 

fuse pins; the defective pins were 

replaced. Therefore, DLH supports the 

repetitive inspections of the fuse pins. 

Request for Credit for Initial Inspection 

DLH asks that the initial inspection 

procedure done per Maintenance 

Planning Document (MPD) Item 54– 

322–01, of the applicable airplane 

maintenance manual (AMM), be 

acceptable for compliance with the 

initial inspection required by the 

NPRM. In addition, DLH does not 

support the compliance times for the 

initial inspection. DLH feels that the 

inspection of the fuse pins done during 

its maintenance check per the AMM 

provides the same level of safety as the 

initial inspection done per the service 

bulletin referenced in the NPRM. 

We do not agree. The AMM only 

includes procedures for access and does 

not provide inspection procedures; 

therefore, the service bulletin provides 

the inspection procedures. If DLH 

believes that its inspection procedures 

provide an acceptable alternative, under 

the provisions of paragraph (g) of this 

AD, we will consider requests for 

approval of an alternative method of 

compliance if sufficient data are 

submitted to substantiate that the 

alternative inspection would provide an 

acceptable level of safety. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

616 airplanes of U.S. registry. We also 

estimate that it will take 4 work-hours 

per product to comply with the 

inspection in this AD. The average labor 

rate is $80 per work-hour. Based on 

these figures, we estimate the cost of 


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59494 Federal Register / Vol. 73, No. 197 / Thursday, October 9, 2008 / Rules and Regulations 

this AD to the U.S. operators to be 

$197,120, or $320 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2008–21–03 Boeing: Amendment 39–15687. 

Docket No. FAA–2008–0357; Directorate 

Identifier 2008–NM–005–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective November 13, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

737–300, –400, and –500 series airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD results from a report of 

corrosion damage of the chrome runout on 

the head side found on all four midspar fuse 

pins of the nacelle strut. Additionally, a large 

portion of the chrome plate was missing from 

the corroded area of the shank. We are 

issuing this AD to detect and correct damage 

of the fuse pins of the inboard and outboard 

midspar fittings of the nacelle strut, which 

could result in reduced structural integrity of 

the fuse pins and consequent loss of the strut 

and separation of the engine from the 

airplane. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Repetitive Inspections/Corrective Actions 

(f) At the applicable time specified in 

paragraph 1.E., ‘‘Compliance’’ of Boeing 

Special Attention Service Bulletin 737–54– 

1044, dated December 10, 2007; except, 

where the service bulletin specifies a 

compliance time after the date on the service 

bulletin, this AD requires compliance within 

the specified compliance time after the 

effective date of this AD: Do a detailed 

inspection for discrepancies of the fuse pins 

of the inboard and outboard midspar fittings 

of the nacelle strut by doing all the actions, 

including all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of the service bulletin. Do all 

applicable corrective actions before further 

flight. Repeat the inspection at the time 

specified in paragraph 1.E. of the service 

bulletin. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: 

Allen Rauschendorfer, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6432; fax (425) 917–6590; has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane. 

Material Incorporated by Reference 

(h) You must use Boeing Special Attention 

Service Bulletin 737–54–1044, dated 

December 10, 2007, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; or at 

the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 29, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–23658 Filed 10–8–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30630; Amdt. No. 3289] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 


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