Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Rules and Regulations 73689 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

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

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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 approval letter 

must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. You are required 

to ensure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0262, dated October 30, 2013, 

for related information. You may examine the 

MCAI on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–0979. 

(j) 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 this AD specifies otherwise. 

(i) Dassault Mandatory Service Bulletin 

F10–318, dated October 30, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.com. 

(4) You may view 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. 

(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 

November 26, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–29122 Filed 12–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0753; Directorate 

Identifier 2013–CE–025–AD; Amendment 

39–17677; AD 2013–24–03] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation Airplanes 

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 1900, 1900C, and 

1900D airplanes. This AD was prompted 

by reports of cracking in the front spar 

cap angles and hat section structure of 

the vertical stabilizer. This AD requires 

inspections of the vertical stabilizer spar 

angles and hat section for cracks with 

corrective actions as necessary. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective January 13, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 13, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Beechcraft 

Corporation at address: 10511 E. 

Central, Wichita, Kansas 67206; phone: 

(800) 429–5372 or (316) 676–3140; 

Internet: http://www.beechcraft.com/

customer_support/contact_us/. You may 

view this 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: Paul 

Chapman, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; phone: (316) 946–4152; 

fax: (316) 946–4107; email: 

paul.chapman@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on August 27, 2013 (78 FR 

52870). The NPRM proposed to require 

doing visual inspections of the vertical 

stabilizer spar angles and hat section for 

cracks and taking corrective actions as 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Further Support for the AD 

Scott Lewis suggested that the number 

of cracks reported may not be accurate. 

The commenter stated that his fleet had 

53 cracks, which is a much higher 

percentage of airplanes cracked than the 

56 cracks reported in the 140 airplanes 

that Beechcraft reported to the FAA. 

The commenter proposed no changes to 

the AD. 

We agree that the percentage of cracks 

reported may be low. This further 

justifies the need for the AD action and 

therefore, no changes to the final rule 

are necessary. 

Costs of Compliance Too Low 

Scott Lewis stated the costs supplied 

by Beechcraft are too low and that the 

actual costs are running $5,983 per side 

for the spar cap angles plus $9,212 for 

engineer support for a total of $15,195. 

This is compared to the $3,150 cited in 

the NPRM. This does not include the 

cost of the hat section if it requires 

repair. 


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73690 Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Rules and Regulations 

We agree with the commenter. After 

re-verifying the cost estimate with 

Beechcraft, they have corrected the costs 

as follows: 

• $6,000 per side for the spar repair 

kit; 

• Around $15,000 for engineering 

support since these are not standard 

repairs. 

We have changed the AD accordingly. 

Continued Flight Before Repair 

Provided Cracks Do Not Propagate 

Scott Lewis stated that he had been 

issued up to an additional 2,700 flight 

hours after a crack was found as long as 

the crack did not propagate. Although 

no request to change the NPRM was 

made, the FAA infers that the 

commenter wants to add the provision 

of flight with known cracks provided 

any known crack does not propagate. 

The FAA does not agree. The FAA’s 

Small Airplane Directorate does not 

allow further flight with known cracks 

in critical structure without additional 

substantiating data. Advisory Circular 

(AC) 23–13A, Chapter 6, dated 

September 29, 2005, describes what 

additional data is required to allow 

flight with known cracks (found on the 

Internet at http://rgl.faa.gov/Regulatory_

and_Guidance_Library/

rgAdvisoryCircular.nsf). 

We are making no changes to the AD 

based on this comment. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, 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 NPRM (78 FR 

52870, August 27, 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 52870, 

August 27, 2013). 

Costs of Compliance 

We estimate that this AD affects 400 

airplanes. 

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 

Visual inspection of the vertical stabilizer 

spar angles and hat section.

1.5 work-hours × $85 per hour = $127.50 .. Not applicable .... $127.50 $51,000 

We estimate the following costs to do 

any necessary repairs that are required 

based on the results of the inspection. 

We have no way of determining the 

number of airplanes that might need 

these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair of the spar cap (right hand or 

left hand).

30 work-hours × $85 per hour = 

$2,550.

$6,000 per side plus $15,000 per engineering support.As much as $29,550 if 

both sides needed repair. 

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), 

(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. 

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 airworthiness 

directive (AD): 

2013–24–03 Beechcraft Corporation (type 

certificate previously held by Hawker 

Beechcraft Corporation): Amendment 

39–17677; Docket No. FAA–2013–0753; 

Directorate Identifier 2013–CE–025–AD. 


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Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Rules and Regulations 73691 

(a) Effective Date 

This AD is effective January 13, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following 

Beechcraft Corporation airplanes in table 1 of 

this AD, certificated in any category: 

TABLE 1 TO PARAGRAPH (c) OF THIS

AD—Applicability 

Model Serial Numbers 

1900 ................ UA–3. 

1900C ............. UB–1 through UB–74, UC–1 

through UC–174. 

1900C (C–12J) UD–1 through UD–6. 

1900D ............. UE–1 through UE–439. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the front spar cap angles and hat 

section of the vertical stabilizer structure. We 

are issuing this AD to detect and correct 

cracking in the vertical stabilizer structure, 

which could lead to structural failure of the 

vertical stabilizer and result in loss of 

control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Visual Inspections 

(1) For all airplanes: Within the next 600 

hours time-in-service (TIS) after January 13, 

2014 (the effective date of this AD), inspect 

part number (P/N) 101–640011–3/–4 spar 

angles and P/N 114–640000–25/–26 hat 

section for cracks following the 

Accomplishment Instructions in paragraph 

3.A. of Hawker Beechcraft Mandatory Service 

Bulletin SB 55–4114, dated August 2012. 

(2) For Models 1900 and 1900C airplanes: 

Within 1,200 hours TIS after the initial 

inspection required in paragraph (g)(1) of this 

AD or within 2 years after the initial 

inspection required in paragraph (g)(1) of this 

AD, whichever occurs first, and repetitively 

thereafter at intervals not to exceed 1,200 

hours TIS or 2 years, whichever occurs first, 

inspect P/N 101–640011–3 and P/N 101– 

640011–4 spar cap angles for cracks. Follow 

Procedure 8 under Vertical Stabilizer in the 

‘‘I’’ Check Procedures of Hawker Beechcraft 

Corporation Model 1900/1900C Airliner 

Structural Inspection Manual, Part Number 

98–30937G2, dated May 1, 2013. 

(3) For Models 1900 and 1900C airplanes: 

Within 1,200 hours TIS after the initial 

inspection required in paragraph (g)(1) of this 

AD or within 2 years after the initial 

inspection required in paragraph (g)(1) of this 

AD, whichever occurs first, and repetitively 

thereafter at intervals not to exceed 1,200 

hours TIS or 2 years, whichever occurs first, 

inspect P/N 114–640000–25 and P/N 114– 

640000–26 hat section for cracks. Follow 

Procedure 9 under Vertical Stabilizer in the 

‘‘I’’ Check Procedures of Hawker Beechcraft 

Corporation Model 1900/1900C Airliner 

Structural Inspection Manual, Part Number 

98–30937G2, dated May 1, 2013. 

(4) For Model 1900D airplanes: Within 

1,200 hours TIS after the initial inspection 

required in paragraph (g)(1) of this AD or 

within 2 years after the initial inspection 

required in paragraph (g)(1) of this AD, 

whichever occurs first, and repetitively 

thereafter at intervals not to exceed 1,200 

hours TIS or 2 years, whichever occurs first, 

inspect P/N 101–640011–3 and P/N 101– 

640011–4 spar cap angles for cracks. Follow 

Procedure 6.b. under Vertical Stabilizer 

Canted Stabilizer Station (CSS 69.184 

through VSS 91.10) in the ‘‘I’’ Check 

Procedures of Beechcraft Corporation Model 

1900D Airliner Structural Inspection Manual, 

Part Number 129–590000–65E5, dated May 1, 

2013. 

(5) For Model 1900D airplanes: Within 

1,200 hours TIS after the initial inspection 

required in paragraph (g)(1) of this AD or 

within 2 years after the initial inspection 

required in paragraph (g)(1) of this AD, 

whichever occurs first, and repetitively 

thereafter at intervals not to exceed 1,200 

hours TIS or 2 years, whichever occurs first, 

inspect P/N 114–640000–25 and P/N 114– 

640000–26 hat section for cracks. Follow 

Procedure 6.c. under Vertical Stabilizer 

Canted Stabilizer Station (CSS 69.184 

through VSS 91.10) in the ‘‘I’’ Check 

Procedures of Beechcraft Corporation Model 

1900D Airliner Structural Inspection Manual, 

Part Number 129–590000–65E5, dated May 1, 

2013. 

(h) Repair 

If any cracks are found during any of the 

inspections required in paragraph (g) of this 

AD, to include all subparagraphs, before 

further flight, you must contact Beechcraft 

Corporation to obtain repair instructions 

approved by the Wichita Aircraft 

Certification Office (ACO) specifically for 

compliance with this AD and incorporate 

those instructions. You can find contact 

information for Beechcraft Corporation in 

paragraph (l)(3) of this AD. 

(i) Special Flight Permit 

If cracks are found during any of the 

inspections required in paragraph (g) of this 

AD, to include all subparagraphs, the FAA 

may allow a one-time special flight permit to 

a repair facility depending on the cracking 

found. You must contact Beechcraft 

Corporation and provide them with crack 

detail information for them to determine 

residual strength of the airplane before 

applying to the FAA for a special flight 

permit. You can find contact information for 

Beechcraft Corporation in paragraph (l)(3) of 

this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita ACO, 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 the 

attention of the person identified in 

paragraph (k) of this AD. 

(2) 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. 

(k) Related Information 

For more information about this AD, 

contact Paul Chapman, Aerospace Engineer, 

Wichita Aircraft Certification Office, FAA, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; phone: (316) 946–4152; fax: 

(316) 946–4107; email: paul.chapman@

faa.gov. 

(l) 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 this AD specifies otherwise. 

(i) Hawker Beechcraft Mandatory Service 

Bulletin SB 55–4114, dated August 2012. 

(ii) Hawker Beechcraft Corporation Model 

1900/1900C Airliner Structural Inspection 

Manual, Part Number 98–30937G2, dated 

May 1, 2013. 

(iii) Beechcraft Corporation Model 1900D 

Airliner Structural Inspection Manual, Part 

Number 129–590000–65E5, dated May 1, 

2013. 

(3) For Beechraft Corporation service 

information identified in this AD, contact 

Beechcraft Corporation at address: 10511 E. 

Central, Wichita, Kansas 67206; phone: (800) 

429–5372 or (316) 676–3140; Internet: http:// 

www.beechcraft.com/customer_support/

contact_us/. 

(4) You may view this 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. 

(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 Kanas City, Missouri, on 

November 15, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–29060 Filed 12–6–13; 8:45 am] 

BILLING CODE 4910–13–P 


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