57564 Federal Register / Vol. 74, No. 215 / Monday, November 9, 2009 / Rules and Regulations 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE—Continued 

Service information title Page(s) Revision Date 

PIAGGIO AERO PIAGGIO P.180 AVANTI Maintenance Manual, Report No. 9066, 32–50–00.501 through 506 ............. Not Applicable .................... March 1, 2006. 

PIAGGIO AERO PIAGGIO P.180 AVANTI II Maintenance Manual, Report No. 180–MAN–0200– 

01105, 32–50–00.

Cover .............................. No. A3 ................................ Revised December 19, 2008. 

PIAGGIO AERO PIAGGIO P.180 AVANTI II Maintenance Manual, Report No. 180–MAN–0200– 

01105, 32–50–00.

1 through 8 ..................... Not Applicable .................... June 30, 2005. 

PIAGGIO AERO PIAGGIO P.180 AVANTI II Maintenance Manual, Report No. 180–MAN–0200– 

01105, 32–50–00.

201, 202, and 207 

through 209.

Not Applicable .................... December 19, 2008. 

PIAGGIO AERO PIAGGIO P.180 AVANTI II Maintenance Manual, Report No. 180–MAN–0200– 

01105, 32–50–00.

203 and 205 ................... Not Applicable .................... June 30, 2005. 

PIAGGIO AERO PIAGGIO P.180 AVANTI II Maintenance Manual, Report No. 180–MAN–0200– 

01105, 32–50–00.

204, 206, and 210 

through 216.

Not Applicable .................... September 14, 2007. 

PIAGGIO AERO PIAGGIO P.180 AVANTI II Maintenance Manual, Report No. 180–MAN–0200– 

01105, 32–50–00.

501 through 506 ............. Not Applicable .................... June 30, 2005. 

Issued in Kansas City, Missouri, on 

October 7, 2009. 

Scott A. Horn, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–24651 Filed 11–6–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1026; Directorate 

Identifier 2009–NM–197–AD; Amendment 

39–16084; AD 2009–23–10] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–300, –400, and –500 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to all Boeing Model 737– 

300, –400, and –500 series airplanes. 

The existing AD currently requires 

inspecting to determine if certain 

carriage spindles are installed, repetitive 

inspections for corrosion and 

indications of corrosion on affected 

carriage spindles, and if necessary, 

related investigative and corrective 

actions. The existing AD also provides 

optional terminating action. For certain 

airplanes, this new AD would reinstate 

the requirements of the existing AD. 

This AD results from the exclusion of 

certain carriage spindles from the 

requirements of the existing AD, and 

additional reports of corrosion found on 

carriage spindles that are located on the 

outboard trailing edge flaps. We are 

issuing this AD to detect and correct 

corrosion of the carriage spindle, which 

could result in fracture. Fracture of both 

the inboard and outboard carriage 

spindles, in the forward ends through 

the large diameters, on a flap, could 

adversely affect the airplane’s continued 

safe flight and landing. 

DATES: This AD becomes effective 

November 24, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 24, 2009. 

On August 5, 2008 (73 FR 42259, July 

21, 2008), the Director of the Federal 

Register approved the incorporation by 

reference of a certain other publication 

listed in the AD. 

We must receive any comments on 

this AD by December 24, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1, 

fax 206–766–5680; e-mail me.boecom@ 

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 street address for 

the Docket Office (telephone 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 10, 2008, we issued AD 2008– 

15–05, amendment 39–15617 (73 FR 

42259, July 21, 2008). That AD applies 

to all Boeing Model 737–300, –400, and 

–500 series airplanes. That AD requires 

inspecting to determine if certain 

carriage spindles are installed, repetitive 

inspections for corrosion and 

indications of corrosion on affected 

carriage spindles, and if necessary, 

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Federal Register / Vol. 74, No. 215 / Monday, November 9, 2009 / Rules and Regulations 57565 

related investigative action and 

corrective action. That AD also provides 

optional terminating action. That AD 

resulted from a report of corrosion 

found on carriage spindles that are 

located on the outboard trailing edge 

flaps. The actions specified in that AD 

are intended to detect and correct 

corrosion of the carriage spindle, which 

could result in fracture. Fracture of both 

the inboard and outboard carriage 

spindles, in the forward ends through 

the large diameters, on a flap, could 

adversely affect the airplane’s continued 

safe flight and landing. 

Actions Since Existing AD Was Issued 

Since we issued AD 2008–15–05, we 

approved an alternative method of 

compliance (AMOC), dated December 8, 

2008, to exclude certain carriage spindle 

serial numbers from the inspection 

requirements. This approval was given 

based on information received from 

Boeing indicating that only one supplier 

of the carriage spindles produced 

discrepant coatings, and that the 

carriages produced by the second 

supplier did not have this unsafe 

condition. 

Subsequent to the AMOC approval, 

we were advised that the carriages 

produced by the second supplier may 

have been incorrectly finished, leading 

to over-grinding of the high velocity 

oxy-fuel (HVOF) coating on the spindle. 

The over-grinding of the HVOF coating 

leads to exposure of the base metal, 

which is susceptible to corrosion. We 

also received additional reports of 

corrosion found on the carriage spindles 

that were excluded from the inspection 

requirements in the existing AD. 

Investigation of those carriage spindles 

revealed that discrepant surface 

finishing of the HVOF coating during 

the production process had exposed the 

base metal. The exposed base metal is 

susceptible to corrosion. 

Subsequently, we have determined 

that it is necessary to reinstate the 

inspections of certain carriage spindles 

because those spindles are subject to the 

same unsafe condition. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009. (We referred to 

Boeing Alert Service Bulletin 737– 

57A1304, dated June 2, 2008, as the 

appropriate source of service 

information for accomplishing the 

required actions of AD 2008–15–05.) 

The actions specified in Revision 1 are 

essentially identical to those in Boeing 

Alert Service Bulletin 737–57A1304, 

dated June 2, 2008. Revision 1 

references the effect of the AMOC letter 

discussed previously and adds a new 

table (Table 3) to reflect certain serial 

numbers that also are subject to the 

unsafe condition, but were excluded 

from the inspection requirements under 

the AMOC discussed previously. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. For this reason, we are issuing 

this AD to supersede AD 2008–15–05. 

This new AD retains certain 

requirements of the existing AD. This 

AD would also require accomplishing 

the actions specified in the Relevant 

Service Information described 

previously. 

Interim Action 

We consider this AD interim action. 

We are currently considering requiring 

replacement of all HVOF-coated carriage 

spindles, which will constitute 

terminating action for the repetitive 

inspections required by this AD. 

However, the planned compliance time 

for the replacement would allow enough 

time to provide notice and opportunity 

for prior public comment on the merits 

of the replacement. 

Change to Existing AD 

This AD would retain certain 

requirements of AD 2008–15–05; 

however, the inspection report required 

by paragraph (h) of the existing AD is 

not required by this AD. 

Since AD 2008–15–05 was issued, a 

new paragraph (d) was added to provide 

the Air Transport Association (ATA) of 

America subject code. This code was 

added to make this AD parallel with 

other new AD actions. 

Since AD 2008–15–05 was issued, the 

AD format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2008–15–05 

Corresponding 

requirement in 

this AD 

paragraph (d) ....................... paragraph (e). 

paragraph (e) ....................... paragraph (f). 

paragraph (f) ........................ paragraph (g). 

paragraph (g) ....................... paragraph (h). 

paragraph (i) ........................ paragraph (j). 

paragraph (j) ........................ paragraph (k). 

FAA’s Justification and Determination 

of the Effective Date 

We received additional reports of 

corrosion found on carriage spindles 

that are located on the outboard trailing 

edge flaps and were removed from the 

inspection requirements in the existing 

AD. Investigation of those carriage 

spindles revealed that discrepant 

surface finishing of the HVOF coating 

done during the production process had 

exposed the base metal. The exposed 

base metal is susceptible to corrosion. 

Corrosion occurring on the exposed base 

metal can quickly lead to cracking and 

full fracture of the carriage spindle. 

Fracture of both the inboard and 

outboard carriage spindles, in the 

forward ends through the large 

diameters, on a single flap, could 

adversely affect the airplane’s continued 

safe flight and landing. Because of our 

requirement to promote safe flight of 

civil aircraft and thus, the critical need 

to assure the structural integrity of the 

carriage spindle and the short 

compliance time involved with this 

action, this AD must be issued 

immediately. 

Because an unsafe condition exists 

that requires the immediate adoption of 

this AD, we find that notice and 

opportunity for prior public comment 

hereon are impracticable and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2009–1026; Directorate Identifier 2009– 

NM–197–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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 

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57566 Federal Register / Vol. 74, No. 215 / Monday, November 9, 2009 / Rules and Regulations 

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 the regulation: 

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. 

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. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (14 CFR part 39) as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing amendment 39–15617 (73 FR 

42259, July 21, 2008) and adding the 

following new AD: 

2009–23–10 Boeing: Docket No. FAA–2009– 

1026; Directorate Identifier 2009–NM– 

197–AD; Amendment 39–16084. 

Effective Date 

(a) This AD becomes effective November 

24, 2009. 

Affected ADs 

(b) This AD supersedes AD 2008–15–05, 

Amendment 39–15617. 

Applicability 

(c) This AD applies to all Boeing Model 

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

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from the exclusion of 

certain carriage spindles from the 

requirements of the existing AD, and 

additional reports of corrosion found on 

carriage spindles that are located on the 

outboard trailing edge flaps. The Federal 

Aviation Administration is issuing this AD to 

detect and correct corrosion of the carriage 

spindle, which could result in fracture. 

Fracture of both the inboard and outboard 

carriage spindles, in the forward ends 

through the large diameters, on a flap, could 

adversely affect the airplane’s continued safe 

flight and landing. 

Compliance 

(f) 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 Requirements of AD 2008– 

15–05, With New Service Information 

Inspection To Determine Affected Carriage 

Spindle 

(g) For all airplanes: Within 30 days after 

August 5, 2008 (the effective date of AD 

2008–15–05), inspect the carriage subassembly to determine whether an affected 

carriage spindle with a high velocity oxy-fuel 

(HVOF) thermal coating is installed, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1304, dated June 2, 2008. A review 

of airplane maintenance records is acceptable 

in lieu of this inspection if the part number 

and/or serial number of the carriage can be 

conclusively determined from that review. If 

no affected carriage spindle is installed, no 

further action is required by this paragraph. 

Repetitive Inspections, Related Investigative 

Actions, and Corrective Action 

(h) For airplanes on which any affected 

carriage spindle was determined to be 

installed in accordance with Boeing Alert 

Service Bulletin 737–57A1304, dated June 2, 

2008, as of the effective date of this AD; and 

the spindle is identified in Table 2 of Boeing 

Service Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009: At the later of the 

times specified in paragraphs (h)(1) and 

(h)(2) of this AD, do a detailed inspection (or, 

as an option for the forward end of the 

spindle only, a borescope inspection 

technique may be used) of the spindle for 

corrosion and potential indications of 

corrosion of the carriage spindle, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–57A1304, dated June 2, 

2008; or Boeing Service Bulletin 737– 

57A1304, Revision 1, dated August 11, 2009. 

Do all applicable related investigative and 

corrective actions before further flight. 

Repeat the detailed inspection (or, as an 

option for the forward end of the spindle 

only, the borescope inspection) and certain 

related investigative actions (i.e., the gapcheck or optional non-destructive test (NDT) 

ultrasonic inspection) at the applicable 

compliance times specified in paragraph 1.E. 

of Boeing Alert Service Bulletin 737– 

57A1304, dated June 2, 2008; or Boeing 

Service Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009. 

(1) Within 30 days after August 5, 2008. 

(2) Within 90 days after the installation of 

a new HVOF-coated spindle. 

Note 1: Boeing Alert Service Bulletin 737– 

57A1304, dated June 2, 2008; and Boeing 

Service Bulletin 737–57A1304, Revision 1, 

dated August 11, 2009; reference Boeing 

Alert Service Bulletin 737–57A1277, 

Revision 1, dated November 25, 2003; for 

further guidance on accomplishing the 

related investigative actions. 

New Requirements of This AD 

Repetitive Inspections, Related Investigative 

Actions, and Corrective Action for Certain 

Airplanes 

(i) For airplanes on which a carriage 

spindle having a serial number identified in 

Table 3 of Appendix A of Boeing Service 

Bulletin 737–57A1304, Revision 1, dated 

August 11, 2009, is installed: At the latest of 

the times specified in paragraphs (i)(1), (i)(2), 

and (i)(3) of this AD, as applicable, do a 

detailed inspection (or, as an option for the 

forward end of the spindle only, a borescope 

inspection technique may be used) of the 

spindle for corrosion and potential 

indications of corrosion of the carriage 

spindle, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

57A1304, Revision 1, dated August 11, 2009. 

Do all applicable related investigative and 

corrective actions before further flight. 

Repeat the detailed inspection (or, as an 

option for the forward end of the spindle 

only, the borescope inspection) and related 

investigative actions (i.e., the gap-check or 

optional NDT ultrasonic inspection) at the 

applicable compliance times specified in 

paragraph 1.E. of Boeing Service Bulletin 

737–57A1304, Revision 1, dated August 11, 

2009. 

(1) Within 30 days after the effective date 

of this AD. 

(2) Within 90 days after the installation of 

a new HVOF-coated spindle identified in 

Table 3 of Appendix A of Boeing Service 

Bulletin 737–57A1304, Revision 1, dated 

August 11, 2009. 

(3) Within 90 days after doing an 

inspection in accordance with Boeing Alert 

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Federal Register / Vol. 74, No. 215 / Monday, November 9, 2009 / Rules and Regulations 57567 

Service Bulletin 737–57A1304, dated June 2, 

2008. 

Optional Terminating Action 

(j) Replacement of an HVOF-coated 

carriage spindle with a non-HVOF coated 

carriage spindle, or with a serviceable HVOFcoated carriage spindle with an ‘R’ suffix on 

the serial number, in accordance with Boeing 

Alert Service Bulletin 737–57A1304, dated 

June 2, 2008; or Boeing Service Bulletin 737– 

57A1304, Revision 1, dated August 11, 2009; 

terminates the requirements of this AD for 

that carriage spindle only. 

Parts Installation 

(k) As of August 5, 2008, an HVOF-coated 

spindle without an ‘R’ suffix on the serial 

number may be installed on an airplane 

provided the actions required by paragraph 

(h) or (i) of this AD, as applicable, are done 

on that spindle. 

Alternative Methods of Compliance (AMOCs) 

(l)(1) The Manager, Seattle 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: 

Nancy Marsh, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6440; fax 

(425) 917–6590. Or, e-mail information to 9– 

ANM–Seattle–ACO–AMOC– 

Requests@faa.gov. 

(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 principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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. 

(4) AMOCs approved previously in 

accordance with AD 2008–15–05, are not 

approved as AMOCs for this AD. 

Material Incorporated by Reference 

(m) You must use Boeing Alert Service 

Bulletin 737–57A1304, dated June 2, 2008; 

and Boeing Service Bulletin 737–57A1304, 

Revision 1, dated August 11, 2009; as 

applicable; 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 

Boeing Service Bulletin 737–57A1304, 

Revision 1, dated August 11, 2009, under 5 

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

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Alert Service Bulletin 

737–57A1304, dated June 2, 2008, on August 

5, 2008 (73 FR 42259, July 21, 2008). 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.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 October 

26, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–26581 Filed 11–6–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0165; Directorate 

Identifier 2008–CE–055–AD; Amendment 

39–16075; AD 2009–23–03] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation (Type 

Certificate Previously Held by 

Raytheon Aircraft Company) Models 

1900, 1900C, and 1900D Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) to 

supersede AD 2006–24–11, which 

applies to certain Hawker Beechcraft 

Corporation (HBC) (Type Certificate 

previously held by Raytheon Aircraft 

Company) Models 1900, 1900C, and 

1900D airplanes. AD 2006–24–11 

currently requires you to repetitively 

inspect the forward, vertical, and aft 

flanges of both the left and right wing 

rear spar lower caps for cracks, repair 

any cracks found, and report the 

inspection results to the manufacturer. 

Since we issued AD 2006–24–11, the 

manufacturer has developed a 

modification kit to install on the wing 

rear spar lower caps that will terminate 

the 200-hour repetitive inspection 

required in AD 2006–24–11. 

Consequently, this AD requires 

installing the new modification kits on 

the wing rear spar lower caps and 

terminates the repetitive inspections 

required in AD 2006–24–11 when the 

kits are installed. We are issuing this AD 

to prevent fatigue cracks in the wing 

rear spar lower caps, which could result 

in fatigue failure of the wing rear spar 

lower caps. A rear spar failure could 

result in complete wing failure and the 

wing separating from the airplane. 

DATES: This AD becomes effective on 

December 14, 2009. 

On December 14, 2009, the Director of 

the Federal Register approved the 

incorporation by reference of Hawker 

Beechcraft Mandatory Service Bulletin 

57–3816, Issued: January 2008, listed in 

this AD. 

As of December 11, 2006 (71 FR 

70297, December 4, 2006), the Director 

of the Federal Register approved the 

incorporation by reference of Raytheon 

Mandatory Service Bulletin 57–3815, 

dated Issued: October 2006, listed in 

this AD. 

ADDRESSES: To get the service 

information identified in this AD, 

contact Hawker Beechcraft Corporation, 

Attn: Airline Technical Support, P.O. 

Box 85, Wichita, Kansas 67201; 

telephone: (800) 429–5372; fax: (316) 

676–8745; Internet: http:// 

www.hawkerbeechcraft.com. 

To view the AD docket, go to U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590, or on the Internet at http:// 

www.regulations.gov. The docket 

number is FAA–2009–0165; Directorate 

Identifier 2008–CE–055–AD. 

FOR FURTHER INFORMATION CONTACT: 

Steve Potter, Aerospace Engineer, 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946– 

4124; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On February 19, 2009, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to 

certain HBC Models 1900, 1900C, and 

1900D airplanes. This proposal was 

published in the Federal Register as a 

notice of proposed rulemaking (NPRM) 

on February 27, 2009 (74 FR 8885). The 

NPRM proposed to supersede AD 2006– 

24–11 with a new AD that would 

require you to install modification kits 

on the wing rear spar lower caps. The 

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