Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 23897 

53A2473, Revision 4, dated December 1, 

2011, specifies to contact Boeing for repair 

instructions, the repair instructions must be 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. All 

provisions of AD 2010–14–07 that are not 

specifically referenced in this paragraph 

remain fully applicable and must be 

complied with. 

(2) Accomplishing the inspections, repairs, 

and interim modification in accordance with 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, is an 

acceptable terminating action for the 

corresponding inspections, repairs and 

interim modification at the BS 2598 bulkhead 

required by paragraphs (i), (j), (o), (s), (t), (u), 

and (v) of AD 2010–14–07, Amendment 39– 

16352 (75 FR 38001, July 1, 2010). Where 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, specifies to 

contact Boeing for repair data, the repair data 

must be approved in accordance with the 

procedures specified in paragraph (q) of this 

AD. All provisions of AD 2010–14–07 that 

are not specifically referenced in this 

paragraph remain fully applicable and must 

be complied with. 

(p) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), (i), 

and (n)(2) of this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 747– 

53A2427, Revision 6, dated July 14, 2011, 

provided that the additional actions added in 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, are done 

within the applicable compliance times 

specified in paragraphs (g), (h), and (i) of this 

AD. Boeing Alert Service Bulletin 747– 

53A2427, Revision 6, dated July 14, 2011, is 

not incorporated by reference in this AD. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(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. 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 (r)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(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. 

(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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that 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, and the 

approval must specifically refer to this AD. 

(4) Related portions or applicable 

paragraphs of AMOCs approved previously 

in accordance with AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010), are approved as AMOCs for the 

corresponding provisions of paragraphs (g), 

(h), (i), (j), (k), and (l) of this AD. All new 

actions specified in paragraphs (g), (h), (i), (j), 

(k), and (l) of this AD that are not identified 

in a previously approved AMOC must still be 

done. 

(r) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6428; fax: 425–917–6590; email: 

nathan.p.weigand@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be viewed at the addresses 

specified in paragraphs (s)(3) and (s)(4) of 

this AD. 

(s) 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) Boeing Alert Service Bulletin 747– 

53A2427, Revision 7, dated July 19, 2013. 

(ii) Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011. 

(iii) Boeing Alert Service Bulletin 747– 

53A2837, dated July 13, 2012. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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 March 

17, 2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–07339 Filed 4–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0020; Directorate 

Identifier 2013–CE–039–AD; Amendment 

39–17821; AD 2014–07–07] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

airworthiness directive (AD) 87–02–04 

for British Aerospace (Operations) 

Limited Model HP.137 Jetstream MK.1, 

Jetstream Series 200, and Jetstream 

Series 3101 airplanes. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as cracking of the forward 

main landing gear yoke pintle resulting 

from corrosion pits leading to stress 

corrosion. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective June 3, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 3, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0020; or in person at the Docket 

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 service information identified in 

this AD, contact BAE Systems 

(Operations) Ltd, Customer Information 

Department, Prestwick International 

Airport, Ayrshire, KA9 2RW, Scotland, 

United Kingdom; phone: +44 1292 

675207, fax: +44 1292 675704; email: 

RApublications@baesystems.com; 

Internet: http://

www.jetstreamcentral.com. 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. 


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23898 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 

FOR FURTHER INFORMATION CONTACT

Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4138; fax: (816) 329–4090; email: 

taylor.martin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to add an AD that would apply 

to British Aerospace (Operations) 

Limited Model HP 137 Jetstream MK1, 

Jetstream Series 200, and Jetstream 

Series 3101 airplanes. The NPRM was 

published in the Federal Register on 

January 15, 2014 (79 FR 2593), and 

proposed to supersede AD 87–02–04, 

Amendment 39–5497 (51 FR 47211, 

December 31, 1986). 

The NPRM (79 FR 2593, January 15, 

2014) proposed to correct an unsafe 

condition for the specified products and 

was based on mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country. The MCAI states that: 

Prompted by occurrences of the main 

landing gear (MLG) yoke pintle housing 

cracking, the United Kingdom Civil Aviation 

Authority (UK CAA) issued AD G–003–01–86 

to require repetitive inspections to identify 

any crack in the yoke pintle housing on MLG 

fitted to Jetstream 3100 aeroplanes in 

accordance with BAE Systems (Operations) 

Ltd Service Bulletin (SB) 32–A–JA851226, 

and depending on findings, corrective action. 

After that AD was issued, an occurrence of 

Jetstream 3100 MLG failure was reported 

after landing. The subsequent investigation 

revealed stress corrosion cracking of the MLG 

yoke pintle housing as a root cause of the 

MLG failure. Furthermore, the investigation 

report recommended a review of the 

effectiveness of UK CAA AD G–003–01–86 in 

identifying cracks in the yoke pintle housing 

on MLG fitted to Jetstream 3100 aeroplanes. 

Degradation of the surface protection by 

abrasion can occur when the forward face of 

the yoke pintle rotates against the pintle 

bearing, which introduces corrosion pits and, 

consequently, stress corrosion cracking. 

This condition, if not detected and 

corrected, could lead to structural failure of 

the MLG, possibly resulting in loss of control 

of the aeroplane during take-off or landing 

runs. 

To provide protection of the affected area 

of the MLG assembly spigot housing, BAE 

Systems (Operations) Ltd issued SB 32– 

JM7862 to provide instructions for 

installation of a protective washer, fitted at 

the forward spigot on both, left hand (LH) 

and right hand (RH), MLG. Consequently, 

BAE Systems (Operations) Ltd issued SB 32– 

A–JA851226 at Revision 5 to provide 

additional accomplishment instructions for 

Non-destructive testing inspection (NDT) of 

MLG equipped with the protective washer 

installed in accordance with BAE Systems 

(Operations) Ltd SB 32–JM7862 and to 

introduce reference to MLG manufacturer 

APPH Ltd SB 32–19 at Revision 4, providing 

instructions for re-protection of the yoke 

pintle. 

For the reasons described above, this AD 

retains the requirements of AD G–003–01–86, 

which is superseded, and requires 

implementation of revised inspection 

requirements, and depending on findings, 

corrective action. This AD introduces an 

optional modification, which constitutes 

terminating action for the inspections 

required by this AD. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0020- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM 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 the 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 (79 FR 2593, 

January 15, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD will affect 

44 products of U.S. registry. We also 

estimate that it would take about 14 

work-hours per product to comply with 

the inspection requirements of this AD. 

The average labor rate is $85 per workhour. 

Based on these figures, we estimate 

the cost of this AD on U.S. operators to 

be $52,360, or $1,190 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours and require parts 

costing $5,000, for a cost of $5,850 per 

product for repairs. We have no way of 

determining the number of products 

that may need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We 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 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0020; 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 the NPRM, 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. 

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: 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 23899 

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 39–5497 (51 FR 

47211, December 31, 1986) and adding 

the following new AD: 

2014–07–07 British Aerospace (Operations) 

Limited: Amendment 39–17821; Docket 

No. FAA–2014–0020; Directorate 

Identifier 2013–CE–039–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 3, 2014. 

(b) Affected ADs 

This AD supersedes AD 87–02–04, 

Amendment 39–5497 (51 FR 47211, 

December 31, 1986. 

(c) Applicability 

This AD applies to British Aerospace 

(Operations) Limited Model HP.137 Jetstream 

Mk.1, Jetstream Series 200, and Jetstream 

Series 3101 airplanes, all serial numbers, 

certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as cracking of 

the forward main landing gear (MLG) yoke 

pintle that resulted from corrosion pits 

leading to stress corrosion. We are issuing 

this AD to prevent failure of the MLG, which 

could result in loss of control of the airplane 

during take-off or landing. 

(f) Actions and Compliance 

Unless already done, do the following 

actions specified in paragraphs (f)(1) through 

(f)(11) of this AD: 

(1) For airplanes that were affected by AD 

87–02–04, Amendment 39–5497 (51 FR 

47211, December 31, 1986): At the next 1,200 

MLG flight cycle repetitive inspection that 

would have been required by AD 87–02–04 

or within the next 12 months after the last 

1,200 MLG flight cycle repetitive inspection 

that would have been required by AD 87–02– 

04, whichever occurs first, and repetitively 

thereafter at intervals not to exceed 1,200 

MLG flight cycles or 12 months, whichever 

occurs first, do a nondestructive testing 

(NDT) inspection of each MLG assembly 

cylinder attachment spigot housing following 

the Accomplishment Instructions in APPH 

Ltd. Service Bulletin No. 32–19, Revision 4, 

dated April 3, 2013, and British Aerospace 

Jetstream Series 3100 & 3200 Service Bulletin 

32–A–JA851226, Revision 5, dated April 30, 

2013. 

(2) For airplanes that were not affected by 

AD 87–02–04, Amendment 39–5497 (51 FR 

47211, December 31, 1986): Within the next 

300 MLG flight cycles after June 3, 2014 (the 

effective date of this AD) or within the next 

3 months after June 3, 2014 (the effective date 

of this AD) or at the next overhaul of the 

MLG after June 3, 2014 (the effective date of 

this AD), whichever occurs first, and 

repetitively thereafter at intervals not to 

exceed 1,200 MLG flight cycles or 12 months, 

whichever occurs first, do a NDT inspection 

of each MLG assembly cylinder attachment 

spigot housing following the 

Accomplishment Instructions in APPH Ltd. 

Service Bulletin No. 32–19, Revision 4, dated 

April 3, 2013, and British Aerospace 

Jetstream Series 3100 & 3200 Service Bulletin 

32–A–JA851226, Revision 5, dated April 30, 

2013. 

(3) For all airplanes: Within 300 landings 

after a heavy or abnormal landing, conduct 

a NDT inspection of each MLG assembly 

cylinder attachment spigot following 

Accomplishment Instructions in APPH Ltd. 

Service Bulletin No. 32–19, Revision 4, dated 

April 3, 2013, and British Aerospace 

Jetstream Series 3100 & 3200 Service Bulletin 

32–A–JA851226, Revision 5, dated April 30, 

2013. 

(4) For all airplanes: If any crack is found 

during any inspection required in paragraphs 

(f)(1), (f)(2), or (f)(3) of this AD, before further 

flight, take all necessary corrective actions 

following the Accomplishment Instructions 

in APPH Ltd. Service Bulletin No. 32–19, 

Revision 4, dated April 3, 2013, and British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–A–JA851226, Revision 5, 

dated April 30, 2013. 

(5) For all airplanes: Within 300 MLG 

flight cycles or 3 months, whichever occurs 

first after each NDT inspection required in 

paragraph (f)(1) or (f)(2) of this AD, as 

applicable, and repetitively thereafter at 

intervals not to exceed 300 MLG flight cycles 

or 3 months, whichever occurs first, do a 

visual inspection of each MLG following the 

Accomplishment Instructions in APPH Ltd. 

Service Bulletin No. 32–19, Revision 4, dated 

April 3, 2013, and British Aerospace 

Jetstream Series 3100 & 3200 Service Bulletin 

32–A–JA851226, Revision 5, dated April 30, 

2013. 

(6) For all airplanes: If any discrepancy is 

found during any visual inspection required 

in paragraph (f)(5) of this AD, before further 

flight, take all necessary corrective actions 

following the Accomplishment Instructions 

in APPH Ltd. Service Bulletin No. 32–19, 

Revision 4, dated April 3, 2013, and British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–A–JA851226, Revision 5, 

dated April 30, 2013. 

(7) For all airplanes with a MLG 

incorporating a microswitch hole: Within the 

next 10,600 MLG flight cycles since new and 

repetitively thereafter at intervals not to 

exceed 1,200 MLG flight cycles, do a NDT 

inspection of each MLG microswitch hole 

following the Accomplishment Instructions 

in APPH Ltd. Service Bulletin No. 32–40, 

Revision 1, dated February 2003, and Part C, 

paragraph (2)(b) of British Aerospace 

Jetstream Series 3100 & 3200 Service Bulletin 

32–A–JA851226, Revision 5, dated April 30, 

2013. 

(8) For all airplanes: If any crack is found 

during any NDT inspection required in 

paragraph (f)(7) of this AD, before further 

flight, take all necessary corrective actions 

following the Accomplishment Instructions 

in APPH Ltd. Service Bulletin No. 32–40, 

Revision 1, dated February 2003, and British 

Aerospace Jetstream Series 3100 & 3200 

Service Bulletin 32–A–JA851226, Revision 5, 

dated April 30, 2013. 

(9) For all airplanes: Doing all necessary 

corrective actions required in paragraphs 

(f)(4), (f)(6), and (f)(8) of this AD does not 

constitute terminating action for the 

inspections required by this AD. 

(10) For all airplanes: Modification of each 

MLG cylinder following Jetstream Service 

Bulletin 32–JA880340, original issue, dated 

January 6, 1989, constitutes terminating 

action for the inspections required by this AD 

for that MLG. 

(11) For all airplanes: The compliance 

times in paragraphs (f)(2), (f)(3), (f)(5), and 

(f)(7) of this AD are presented in flight cycles 

(landings). If the total flight cycles have not 

been kept, multiply the total number of 

airplane hours time-in-service (TIS) by 0.75 

to calculate the cycles. For the purposes of 

this AD: 

(i) 100 hours TIS × .75 = 75 cycles; and 

(ii) 1,000 hours TIS × .75 = 750 cycles. 

(g) Credit for Actions Done in Accordance 

With Previous Service Information 

This AD allows credit for the initial 

inspection required in paragraph (f)(7) of this 

AD if done before June 3, 2014 (the effective 

date of this AD) following APPH Ltd. Service 

Bulletin 32–40, at Initial Issue dated June 21, 

1989. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4138; fax: (816) 329– 

4090; email: taylor.martin@faa.gov. 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. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 


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23900 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2013–0208, dated 

September 10, 2013, for related information. 

The MCAI can be found in the AD docket on 

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

#!documentDetail;D=FAA-2014-0020-0002. 

For availability information about APPH Ltd. 

Service Bulletin 32–40, at Initial Issue dated 

June 21, 1989, which is not incorporated by 

reference, use the contact information in 

paragraphs (j)(4) and (j)(5). 

(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 the AD specifies otherwise. 

(i) APPH Ltd. Service Bulletin No. 32–19, 

Revision 4, dated April 3, 2013. 

(ii) APPH Ltd. Service Bulletin No. 32–40, 

Revision 1, dated February 2003. 

(iii) British Aerospace Jetstream Series 

3100 & 3200 Service Bulletin 32–A– 

JA851226, Revision 5, dated April 30, 2013. 

(iv) Jetstream Service Bulletin 32– 

JA880340, original issue, dated January 6, 

1989. 

(3) For British Aerospace (Operations) 

Limited and Jetstream service information 

identified in this AD, contact BAE Systems 

(Operations) Ltd, Customer Information 

Department, Prestwick International Airport, 

Ayrshire, KA9 2RW, Scotland, United 

Kingdom; phone: +44 1292 675207, fax: +44 

1292 675704; email: RApublications@

baesystems.com; Internet: http://

www.jetstreamcentral.com. 

(4) For APPH Ltd. service information 

identified in this AD, contact APPH Ltd. 

Engineering Division, Unit 1, Pembroke 

Court, Chancellor Road, Manor Park, 

Runcorn, Cheshire, WA7 1TG, England; 

phone: +44 01928 532600; fax: +44 01928 

579626; Internet: http://apph.com/contactus/customer-support/. 

(5) You may view this service information 

at 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. 

(6) 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 Kansas City, Missouri, on April 

4, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–09540 Filed 4–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0233; Directorate 

Identifier 2014–NM–053–AD; Amendment 

39–17825; AD 2014–08–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–03– 

08 for all Airbus Model A318, A319, 

A320, and A321 series airplanes. AD 

2014–03–08 required an inspection to 

determine the part number of the 

interconnecting struts installed on the 

wings, identifying the part number and 

the serial number of the associated 

target and proximity sensor if 

applicable, and replacing or reidentifying the flap interconnecting 

strut if applicable. This new AD corrects 

a typographical error that affects the 

definition of a serviceable 

interconnecting strut. This AD was 

prompted by a report that an 

investigation showed that when a 

certain combination of a target/

proximity sensor serial number is 

installed on a flap interconnecting strut, 

a ‘‘target FAR’’ signal cannot be detected 

when it reaches the mechanical end 

stop of the interconnecting strut. We are 

issuing this AD to detect and correct a 

latent failure of the flap down drive 

disconnection due to an already-failed 

interconnecting strut sensor, which 

could result in asymmetric flap panel 

movement and consequent loss of 

control of the airplane. 

DATES: This AD becomes effective May 

14, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 26, 2014 (79 FR 9398, 

February 19, 2014). 

We must receive comments on this 

AD by June 13, 2014. 

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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; Internet http://

www.airbus.com. You may view this 

referenced 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0233; 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 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. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM 116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 22, 2014, we issued AD 

2014–03–08, Amendment 39–17745 (79 

FR 9398, February 19, 2014). AD 2014– 

03–08 applied to all Airbus Model 

A318, A319, A320, and A321 series 


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