51050 Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations 

2013–16–07 Eurocopter France Helicopters: 

Amendment 39–17545; Docket No. 

FAA–2013–0353; Directorate Identifier 

2008–SW–029–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) models AS332C, AS332L, 

AS332L1, AS332L2, and EC225LP 

helicopters, serial numbers (S/N) up to and 

including 2680 and S/N 9000 through 9009, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

interference between the tail gearbox (TGB) 

attachment bolt and the structure fitting. This 

condition could result in insufficient 

tightening of the TGB casing, damage to the 

TGB attachment, cracking under the 

attachment bolt, loss of the TGB and 

consequently, loss of helicopter control. 

(c) Effective Date 

This AD becomes effective September 24, 

2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 50 hours time-in-service (TIS): 

(1) Inspect the TGB aft attachment fitting 

to measure the dimension for a blind hole as 

follows: 

(i) Remove the TGB attachment bolt (c) but 

retain washer (d) as depicted in Detail A, 

Figure 1, of Eurocopter Emergency Alert 

Service Bulletin (EASB) No. 53.01.58 and 

EASB No. 53A012, both Revision 1, and both 

dated January 4, 2008. 

(ii) Use a depth gauge to measure 

dimension ‘‘x’’ between the top face of the 

washer (d) and the bottom of aft fitting (a) as 

depicted in Detail A, Figure 1, of the EASB. 

(2) If the measurement is equal to or greater 

than 81 mm, then the blind hole is present. 

Install the TGB attachment bolt (c) with its 

washer (d) as depicted in Detail A, Figure 1, 

of EASB No. 53.01.58 or No. 53A012. Lock 

with lockwire. 

(3) If the measurement is less than 81 mm, 

then the blind hole is missing. Inspect the 

end of the threaded section of bolt (c) for 

chafing or a contact mark, as depicted in 

Area 1, Figure 1, of the EASB. 

(i) If there is no chafing and no contact 

marks, install bolt (c) with washer (d) and 

additional washer (2) as depicted in Detail B, 

Figure 1, of EASB No. 53.01.58 or No. 

53A012. 

(ii) If there is chafing or a contact mark, 

replace the TGB attachment bolt (c) with an 

airworthy bolt and install with washer (d) 

and additional washer (2) as depicted in 

Detail B, Figure 1, of EASB No. 53.01.58 or 

No. 53A012. Lock with lockwire. 

(iii) Within the next 825 hours TIS, replace 

the TGB aft attachment fitting with an 

airworthy attachment fitting. 

(4) Inspect the right and left attachment 

points of the TGB forward attachment to 

measure the dimension for a blind hole, as 

follows: 

(i) Remove both TGB attachment bolts (c) 

but retain washers (d), as depicted in Detail 

A, Figure 2, of EASB No. 53.01.58 or No. 

53A012. 

(ii) Use a depth gauge to measure 

dimension ‘‘x’’ between the top face of 

washer (d) and the bottom of forward fitting 

(b) at the right and left attachment points, as 

depicted in Detail A, Figure 2, of EASB No. 

53.01.58 or No. 53A012. 

(5) If both measurements are equal to or 

greater than 81 mm, then the blind hole is 

present. Install TGB attachment bolt (c) with 

its washer (d), as depicted in Detail A, Figure 

2, of EASB No. 53.01.58 or No. 53A012. Lock 

with lockwire. 

(6) If one or both measurements are less 

than 81 mm, then the blind hole is missing. 

Inspect the end of the threaded section of 

each bolt (c) for chafing or a contact mark, 

as depicted in Area 1, Figure 2 of EASB No. 

53.01.58 or No. 53A012. 

(i) If there is no chafing and no contact 

marks, for each attachment point, install bolt 

(c) with washer (d) and additional washer (2), 

as depicted in Detail B, Figure 2, of EASB No. 

53.01.58 or No. 53A012. 

(ii) If there is chafing or a contact mark, 

replace each the TGB attachment bolt (c) 

with an airworthy bolt and install bolt (1) 

with washer (d) and additional washer (2), as 

depicted in Detail B, Figure 2, of EASB No. 

53.01.58 or No. 53A012. Lock with lockwire. 

(iii) Within the next 825 hours TIS, replace 

the TGB forward attachment fitting with an 

airworthy attachment fitting. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in the 

Direction Ge ́ne ́rale de L’Aviation Civile 

(DGAC) France AD No F–2007–027, dated 

January 2, 2008. You may view the DGAC AD 

in the AD Docket on the Internet at http:// 

www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520, Tail Rotor Gearbox. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter EASB No. 53.01.58, Revision 

1, dated January 4, 2008. 

(ii) Eurocopter EASB No. 53A012, Revision 

1, dated January 4, 2008. 

Note 1 to paragraph (i)(2): Eurocopter 

EASB No. 53.01.58 and No. 53A012, both 

Revision 1, and both dated January 4, 2008, 

are co-published as one document along with 

Eurocopter EASB No. 53.00.58 and No. 

53A011, also both Revision 1, and both dated 

January 4, 2008, which are not incorporated 

by reference in this AD. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

that is incorporated by reference in the AD 

Docket on the Internet at http://

www.regulations.gov. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on July 31, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19159 Filed 8–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0297; Directorate 

Identifier 2012–NM–205–AD; Amendment 

39–17550; AD 2013–16–12] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–102, 

–103, and –106 airplanes. This AD was 

prompted by a report of cracking in a 

lower longeron in a nacelle. This AD 

requires repetitive inspections for 

cracking of the lower longerons in the 

nacelles, and replacement with new 

longerons or repair if necessary. 


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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations 51051 

Additionally, this AD specifies an 

optional terminating action. We are 

issuing this AD to detect and correct 

such cracking, which could result in 

degradation of the structural integrity of 

the nacelle and possible collapse of the 

main landing gear (MLG). 

DATES: This AD becomes effective 

September 24, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 24, 2013. 

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: 

Jeffrey Zimmer, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7306; fax (516) 794–5531. 

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. The 

NPRM was published in the Federal 

Register on April 9, 2013 (78 FR 21079). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. Transport Canada Civil 

Aviation (TCCA), which is the aviation 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2012–27, dated November 2, 2012 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

There has been one in-service report where 

a nacelle lower longeron was found to be 

cracked during a routine maintenance 

inspection. The investigation determined that 

the crack initiated from the right-hand side 

(RHS) drain hole. Fatigue testing has 

indicated that both the RHS and left-hand 

side (LHS) longerons are vulnerable to fatigue 

cracking. Failure of the nacelle lower 

longeron would result in a degradation of the 

structural integrity of the nacelle and could 

potentially lead to collapse of the main 

landing gear (MLG). 

This [Canadian] AD mandates initial and 

repeat inspections [for cracking] of the RHS 

and LHS nacelle lower longerons until the 

terminating action is accomplished. 

The initial inspection may be either a 

detailed inspection or a bolt-hole eddy 

current (BHEC) inspection. The 

repetitive inspection is a BHEC 

inspection. The corrective action is 

replacement of the longeron with a new 

longeron or repair. The optional 

terminating action is replacement of the 

nacelle lower longerons, and cold 

working of the drain holes. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 21079, April 9, 2013) or on the 

determination of the cost to the public. 

Changes to Service Information 

References 

Bombardier, Inc. has issued revised 

service information, which specifies 

that no additional actions are necessary 

to address the identified unsafe 

condition. We have revised this AD to 

reference Bombardier Service Bulletin 

8–54–39, Revision B, dated March 13, 

2013, as the appropriate source of 

service information for accomplishing 

the required actions. 

We have also added Bombardier 

Service Bulletin 8–54–39, Revision A, 

dated August 2, 2012, to paragraph (k) 

of this AD, which provides credit for 

actions performed before the effective 

date of this AD. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously– 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

21079, April 9, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 21079, 

April 9, 2013). 

Costs of Compliance 

We estimate that this AD affects 51 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product Cost on U.S. operators 

Repetitive Inspections 21 work-hours × $85 per hour = $1,785 

per inspection cycle.

$0 $1,785 per inspection 

cycle.

$91,035 per inspection cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 100 work-hours × $85 per hour = $8,500 ................................................. $23,849 $32,349 

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 


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51052 Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations 

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 that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. 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 this AD, the MCAI, 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. 

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: 

2013–16–12 Bombardier, Inc.: Amendment 

39–17550. Docket No. FAA–2013–0297; 

Directorate Identifier 2012–NM–205–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 24, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103 airplanes, and airplanes 

converted to Model DHC–8–106 in 

accordance with Bombardier Service Bulletin 

8–92–07 or Bombardier Service Bulletin 8– 

92–08, serial numbers 003 through 287 

inclusive, with pre-modification 8/1593 

nacelle lower longeron installed; certificated 

in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Reason 

This AD was prompted by a report of 

cracking in a lower longeron in a nacelle. We 

are issuing this AD to detect and correct such 

cracking, which could result in degradation 

of the structural integrity of the nacelle and 

possible collapse of the main landing gear 

(MLG). 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Initial Inspection 

At the applicable time specified in 

paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this 

AD: Do a detailed visual inspection or a bolthole eddy current (BHEC) test for cracking of 

each nacelle lower longeron, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–54–39, 

Revision B, dated March 13, 2013. 

(1) For Model DHC–8–102 and -103 

airplanes that have accumulated 35,000 total 

flight cycles or less as of the effective date 

of this AD: Within 5,000 flight cycles after 

the effective date of this AD, but not to 

exceed 36,000 total flight cycles. 

(2) For Model DHC–8–102 and -103 

airplanes that have accumulated more than 

35,000 total flight cycles as of the effective 

date of this AD: Within 1,000 flight cycles 

after the effective date of this AD. 

(3) For Model DHC–8–106 airplanes with 

the Pre-Modification 8/1641 configuration, 

within 500 flight cycles after the effective 

date of this AD. 

(4) For Model DHC–8–106 airplanes with 

the Post-Modification 8/1641 configuration, 

within 5,000 flight cycles after the effective 

date of this AD. 

(h) Repetitive BHEC Testing 

After accomplishment of the actions 

required by paragraph (g) of this AD, at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD: Do repetitive BHEC 

testing for cracking of each nacelle lower 

longeron, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–54–39, Revision B, dated 

March 13, 2013, until the terminating action 

specified in paragraph (j) of this AD is done. 

(1) For Model DHC–8–102 and -103 

airplanes, at intervals not to exceed 2,500 

flight cycles. 

(2) For Model DHC–8–106 airplanes, at 

intervals not to exceed 1,854 flight cycles. 

(i) Replacement or Repair of Crack Longeron 

If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, replace any 

cracked nacelle lower longeron with a new 

longeron, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–54–39, Revision B, dated 

March 13, 2013; or repair the longeron using 

a method approved by either the Manager, 

New York ACO, ANE–170, FAA, or 

Transport Canada Civil Aviation (TCCA) (or 

its delegated agent). 

(j) Optional Terminating Action 

Accomplishment of the actions specified in 

paragraphs (j)(1) and (j)(2) of this AD 

constitutes terminating action for the 

repetitive BHEC testing specified in 

paragraph (h) of this AD for that longeron 

only. 

(1) Replacement of the nacelle lower 

longeron, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–54–39, Revision B, dated 

March 13, 2013. 

(2) Cold working of the drain holes, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–54–39, Revision B, dated March 13, 2013. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (h) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 8–54–39, dated March 14, 2012; or 

using Bombardier Service Bulletin 8–54–39, 

Revision A, dated August 2, 2012; which are 

not incorporated by reference in this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7300; fax (516) 

794–5531. Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. The AMOC 


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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations 51053 

approval letter must specifically reference 

this AD. 

(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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information Canadian 

Airworthiness Directive CF–2012–27, dated 

November 2, 2012, for related information, 

which can be found in the AD docket on the 

Internet at http://www.regulations.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the address specified in 

paragraphs (n)(3) and (n)(4) of this AD. You 

may review copies of this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

Part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bombardier Service Bulletin 8–54–39, 

Revision B, dated March 13, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

1, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19157 Filed 8–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1180; Directorate 

Identifier 2012–CE–032–AD; Amendment 

39–17539; AD 2013–16–01] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation and Hawker Beechcraft 

Corporation 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Beechcraft Corporation (type certificate 

previously held by Hawker Beechcraft 

Corporation) Models 58, 95–C55, E55, 

and 56TC airplanes; and Hawker 

Beechcraft Corporation Models 58P and 

58TC airplanes (both type certificates 

previously held by Raytheon Aircraft 

Company). This AD was prompted by 

reports of elevator balance weights 

becoming loose or failing because the 

balance weight material was under 

strength and did not meet material 

specifications. This AD requires 

inspections of elevator balance weights 

and replacement of defective elevator 

balance weights. We are issuing this AD 

to correct the unsafe condition on these 

products. 

DATES: This AD is effective September 

24, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 24, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Beechcraft 

Corporation, B091–A04, 10511 E. 

Central Ave., Wichita, Kansas 67206; 

telephone: 1 (800) 429–5372 or (316) 

676–3140; fax: (316) 676–8027; email: 

tmdc@beechcraft.com; or Internet: 

http://www.beechcraft.com/

customer_support/technical_and_

field_support. You may review copies of 

the referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

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 (phone: 800–647–5527) is 

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: T. 

N. Baktha, Senior Aerospace Engineer, 

FAA, Wichita ACO, 1801 Airport Road, 

Room 100, Wichita, Kansas 67209; 

telephone: (316) 946–4155; fax: (316) 

946–4107; email: t.n.baktha@faa.gov. 

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 the 

specified products. The NPRM (77 FR 

66566, November 6, 2012) proposed to 

require inspections of elevator balance 

weights and replacement of defective 

elevator balance weights. We followed 

the NPRM with a supplemental notice 

of proposed rulemaking (SNPRM) that 

published in the Federal Register on 

May 15, 2013 (78 FR 28540). The 

SNPRM proposed to prohibit the 

installation of designated spare parts 

and to clarify applicability. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(78 FR 28540, May 15, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (78 FR 

28540, May 15, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Costs of Compliance 

We estimate that this AD affects 1,326 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


sroberts on DSK5SPTVN1PROD with RULES